diff --git a/UnicadoGUI/Backend/output_files/logFiles/calculatePolar.log b/UnicadoGUI/Backend/output_files/logFiles/calculatePolar.log
new file mode 100644
index 0000000000000000000000000000000000000000..4adc9287fb1aa076d397675f9ee56ff05720828d
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/logFiles/calculatePolar.log
@@ -0,0 +1,55 @@
+*******************************************************************************
+22.01.2024 11:07:05 - Start calculatePolar
+22.01.2024 11:07:05 - Create csvOutput-Directory in program folder: csvFiles\
+22.01.2024 11:07:05 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.01.2024 11:07:05 - Create: MainWing ...
+22.01.2024 11:07:05 - Create: Stabiliser ...
+22.01.2024 11:07:05 - Create: Fin ...
+22.01.2024 11:07:05 - Create: Fuselage ...
+22.01.2024 11:07:05 - Create: InnerRightWingNacelle ...
+22.01.2024 11:07:05 - Create: InnerLeftWingNacelle ...
+22.01.2024 11:07:05 - Start calculation ...
+22.01.2024 11:07:05 - Executing calculatePolar in mode 1: Calculation of polar data
+22.01.2024 11:07:05 - Set panel distribution for the MainWing lifting surface ...
+22.01.2024 11:07:05 - Set panel distribution for the Stabiliser lifting surface ...
+22.01.2024 11:07:05 - -> Total number of panels: 187
+22.01.2024 11:07:05 - Write LILI Input file calcPolar_inc_LL.inp ...(calcPolar_inc_LL.inp)
+22.01.2024 11:07:05 - Start LiftingLine (calcPolar_inc_LL) ... DONE
+22.01.2024 11:07:07 - Read LiftingLine results (calcPolar_inc_LL) ...
+22.01.2024 11:07:07 - Set panel distribution for the MainWing lifting surface ...
+22.01.2024 11:07:07 - Set panel distribution for the Stabiliser lifting surface ...
+22.01.2024 11:07:07 - -> Total number of panels: 187
+22.01.2024 11:07:07 - Write LILI Input file calcPolar_M078_LL.inp ...(calcPolar_M078_LL.inp)
+22.01.2024 11:07:07 - Start LiftingLine (calcPolar_M078_LL) ... DONE
+22.01.2024 11:07:09 - Read LiftingLine results (calcPolar_M078_LL) ...
+22.01.2024 11:07:09 - WARNING: For Ma = 0.20: CL_max=1.58 > CL_max (LI_LI)=1.32. Using Extrapolation!
+22.01.2024 11:07:09 - WARNING: For Ma = 0.50: CL_max=1.45 > CL_max (LI_LI)=1.32. Using Extrapolation!
+22.01.2024 11:07:09 - WARNING: For Ma = 0.58: CL_max=1.41 > CL_max (LI_LI)=1.32. Using Extrapolation!
+
+22.01.2024 11:07:09 - Create Aero-Sections ...
+22.01.2024 11:07:09 - * Section 1 (Surface Segment (1st))
+22.01.2024 11:07:09 - * Section 2 (Surface Segment (last))
+22.01.2024 11:07:09 - * Section 3 (Surface Segment (virtual tip))
+22.01.2024 11:07:09 -
+22.01.2024 11:07:09 - Calculate total drag ...
+22.01.2024 11:07:09 - Method for determining the viscous drag (wing): Raymer.
+22.01.2024 11:07:09 - Method for determining the viscous drag (wing) (other components): Raymer.
+22.01.2024 11:07:09 - Method for determining the wave drag: Mason.
+22.01.2024 11:07:09 - Calculate polar for Ma = 0.20 | CL-Range [-0.30;1.58]
+22.01.2024 11:07:10 - Calculate polar for Ma = 0.50 | CL-Range [-0.30;1.45]
+22.01.2024 11:07:10 - Calculate polar for Ma = 0.58 | CL-Range [-0.30;1.41]
+22.01.2024 11:07:11 - Calculate polar for Ma = 0.68 | CL-Range [-0.30;1.16]
+22.01.2024 11:07:12 - Calculate polar for Ma = 0.73 | CL-Range [-0.30;0.97]
+22.01.2024 11:07:12 - Calculate polar for Ma = 0.76 | CL-Range [-0.30;0.85]
+22.01.2024 11:07:13 - Calculate polar for Ma = 0.78 | CL-Range [-0.30;0.76]
+22.01.2024 11:07:14 - Calculate polar for Ma = 0.79 | CL-Range [-0.30;0.71]
+22.01.2024 11:07:14 - Calculate polar for Ma = 0.83 | CL-Range [-0.30;0.51]
+22.01.2024 11:07:14 - ... total drag has been calculated successfully!
+22.01.2024 11:07:14 - CL_max (t/o) = 2.51
+22.01.2024 11:07:14 - CL_max (ldg) = 2.91
+22.01.2024 11:07:14 - ... calculation finished!
+22.01.2024 11:07:14 - Write output ...
+22.01.2024 11:07:14 - Write XML-Output ...
+22.01.2024 11:07:14 - Create XML-Polar file ...
+22.01.2024 11:07:14 - ERROR: tool level to low (value) ..\projects\CSR\CSR-02\CSR-02.xml/AcftExchangeFile/Aerodynamics/LiftCoefficients/C_LoptimumCruise
+22.01.2024 11:07:14 - Finish calculatePolar
diff --git a/UnicadoGUI/Backend/output_files/logFiles/convergenceLoop.log b/UnicadoGUI/Backend/output_files/logFiles/convergenceLoop.log
new file mode 100644
index 0000000000000000000000000000000000000000..a9f2f1c81ba48c5a4a6abb3056de2b8fa0eb0f33
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/logFiles/convergenceLoop.log
@@ -0,0 +1,2647 @@
+*******************************************************************************
+16.01.2024 10:10:31 - Start convergenceLoop
+16.01.2024 10:10:31 - Create folder for tex-report in project folder: ..\projects\CSR\CSR-02\reporting\reportTeX\
+16.01.2024 10:10:31 - Create folder for html-report in project folder: ..\projects\CSR\CSR-02\reporting\reportHTML\
+16.01.2024 10:10:31 - Create folder for plots in project folder: ..\projects\CSR\CSR-02\reporting\plots\
+16.01.2024 10:10:31 - Create folder for configFiles in project folder: ..\projects\CSR\CSR-02\configFiles\
+16.01.2024 10:10:31 - Create folder for configFilesPreExecution in ConfigFile folder: ..\projects\CSR\CSR-02\configFiles\preExecution\
+16.01.2024 10:10:31 - Create folder for configFilesSetup in ConfigFile folder: ..\projects\CSR\CSR-02\configFiles\setup\
+16.01.2024 10:10:31 - Create folder for configFilesSizing in ConfigFile folder: ..\projects\CSR\CSR-02\configFiles\sizingLoop\
+16.01.2024 10:10:31 - Create folder for configFilesStudy in ConfigFile folder: ..\projects\CSR\CSR-02\configFiles\studyLoop\
+16.01.2024 10:10:31 - Create folder for configFilesPostprocessing in ConfigFile folder: ..\projects\CSR\CSR-02\configFiles\postProcessing\
+16.01.2024 10:10:31 - The folder ../01_initialSizing/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../02_fuselageDesign/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../10_createMissionXML/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../11_wingDesign/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../12_empennageSizing/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../13_engineSizing/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../14_propulsionIntegration/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../15_landingGearDesign/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../21_calculatePolar/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../22_massEstimation/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../23_systemsDesign/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../31_missionAnalysis/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../10_createMissionXML/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../23_systemsDesign/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../31_missionAnalysis/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../51_calculatePerformance/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../52_calculateCosts/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../53_estimateDOC/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../52_calculateCosts/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../54_calculateEmissions/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../91_reportGenerator/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../92_cpacsInterface/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - The folder ../93_designEvaluator/ is not available, but will be tried to checkout from repository.
+16.01.2024 10:10:31 - Fetching missing programs ...
+16.01.2024 10:10:31 - Checking out missing folders from Git repository ssh://git@unicado.ilr.rwth-aachen.de:2222/source/rADDITIONALSOFTWARE.git, branch=master, depth=1
+16.01.2024 10:10:31 - Please be patient...
+16.01.2024 10:10:55 - reportGenerator is checked out into folder ../91_reportGenerator/
+16.01.2024 10:10:55 - cpacsInterface is checked out into folder ../92_cpacsInterface/
+16.01.2024 10:10:55 - designEvaluator is checked out into folder ../93_designEvaluator/
+16.01.2024 10:10:55 - Checking out missing folders from Git repository ssh://git@unicado.ilr.rwth-aachen.de:2222/source/rAIRCRAFTDESIGN.git, branch=master, depth=1
+16.01.2024 10:10:55 - Please be patient...
+16.01.2024 10:11:23 - initialSizing is checked out into folder ../01_initialSizing/
+16.01.2024 10:11:23 - fuselageDesign is checked out into folder ../02_fuselageDesign/
+16.01.2024 10:11:23 - createMissionXML is checked out into folder ../10_createMissionXML/
+16.01.2024 10:11:23 - wingDesign is checked out into folder ../11_wingDesign/
+16.01.2024 10:11:23 - empennageSizing is checked out into folder ../12_empennageSizing/
+16.01.2024 10:11:23 - engineSizing is checked out into folder ../13_engineSizing/
+16.01.2024 10:11:23 - propulsionIntegration is checked out into folder ../14_propulsionIntegration/
+16.01.2024 10:11:23 - landingGearDesign is checked out into folder ../15_landingGearDesign/
+16.01.2024 10:11:23 - calculatePolar is checked out into folder ../21_calculatePolar/
+16.01.2024 10:11:23 - massEstimation is checked out into folder ../22_massEstimation/
+16.01.2024 10:11:23 - systemsDesign is checked out into folder ../23_systemsDesign/
+16.01.2024 10:11:23 - missionAnalysis is checked out into folder ../31_missionAnalysis/
+16.01.2024 10:11:23 - calculatePerformance is checked out into folder ../51_calculatePerformance/
+16.01.2024 10:11:23 - Checking out missing folders from Git repository ssh://git@unicado.ilr.rwth-aachen.de:2222/source/rADDITIONALTOOLS.git, branch=master, depth=1
+16.01.2024 10:11:23 - Please be patient...
+16.01.2024 10:11:29 - calculateCosts is checked out into folder ../52_calculateCosts/
+16.01.2024 10:11:29 - estimateDOC is checked out into folder ../53_estimateDOC/
+16.01.2024 10:11:29 - calculateEmissions is checked out into folder ../54_calculateEmissions/
+16.01.2024 10:11:29 - ... checkout finished.
+16.01.2024 10:11:29 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+16.01.2024 10:11:29 - Start calculation ...
+16.01.2024 10:11:30 - Design Modus 0: Standard-Design. No checks in Sub-Programs!
+16.01.2024 10:11:30 - ----------------------------------------
+16.01.2024 10:11:30 - Setup-Tools ...
+16.01.2024 10:11:30 - Start : initialSizing
+16.01.2024 10:11:31 - Start : fuselageDesign
+16.01.2024 10:11:36 - ----------------------------------------
+16.01.2024 10:11:36 - Sizing-Loop ...
+16.01.2024 10:11:36 - Disable plots in subprograms during design iteration!
+16.01.2024 10:11:36 - Auto-Trim activated!
+16.01.2024 10:11:36 - ----- Start Iteration: 1 -----
+16.01.2024 10:11:36 - Start : createMissionXML
+16.01.2024 10:11:36 - Start : wingDesign
+16.01.2024 10:11:36 - Start : empennageSizing
+16.01.2024 10:11:37 - Start : engineSizing
+16.01.2024 10:11:40 - Start : propulsionIntegration
+16.01.2024 10:11:40 - Start : landingGearDesign
+16.01.2024 10:11:40 - Start : calculatePolar
+16.01.2024 10:11:46 - Start : massEstimation
+16.01.2024 10:11:46 - Start : systemsDesign
+16.01.2024 10:11:47 - Start : missionAnalysis
+16.01.2024 10:12:11 - * residuals (rel. error):
+16.01.2024 10:12:11 - Res. MTOM: 0.0348786
+16.01.2024 10:12:11 - Res. OME: 0.160452
+16.01.2024 10:12:11 - Res. xCG: 1
+16.01.2024 10:12:11 - Res. Missionfuel: 1
+16.01.2024 10:12:11 - * Trim: CM (current) = -0.108285 | i_Tailplane (new) = 0
+16.01.2024 10:12:11 - ----- Start Iteration: 2 -----
+16.01.2024 10:12:11 - Start : createMissionXML
+16.01.2024 10:12:11 - Start : wingDesign
+16.01.2024 10:12:11 - Start : empennageSizing
+16.01.2024 10:12:12 - Start : engineSizing
+16.01.2024 10:12:12 - Start : propulsionIntegration
+16.01.2024 10:12:12 - Start : landingGearDesign
+16.01.2024 10:12:12 - Start : calculatePolar
+16.01.2024 10:12:18 - Start : massEstimation
+16.01.2024 10:12:18 - Start : systemsDesign
+16.01.2024 10:12:18 - Start : missionAnalysis
+16.01.2024 10:12:43 - * residuals (rel. error):
+16.01.2024 10:12:43 - Res. MTOM: 0.0127675
+16.01.2024 10:12:43 - Res. OME: 0.0114131
+16.01.2024 10:12:43 - Res. xCG: 0.00582204
+16.01.2024 10:12:43 - Res. Missionfuel: 0.0267532
+16.01.2024 10:12:43 - * Trim: CM (current) = -0.102399 | i_Tailplane (new) = -2
+16.01.2024 10:12:43 - ----- Start Iteration: 3 -----
+16.01.2024 10:12:43 - Start : createMissionXML
+16.01.2024 10:12:43 - Start : wingDesign
+16.01.2024 10:12:43 - Start : empennageSizing
+16.01.2024 10:12:44 - Start : engineSizing
+16.01.2024 10:12:44 - Start : propulsionIntegration
+16.01.2024 10:12:44 - Start : landingGearDesign
+16.01.2024 10:12:44 - Start : calculatePolar
+16.01.2024 10:12:50 - Start : massEstimation
+16.01.2024 10:12:50 - Start : systemsDesign
+16.01.2024 10:12:50 - Start : missionAnalysis
+16.01.2024 10:13:15 - * residuals (rel. error):
+16.01.2024 10:13:15 - Res. MTOM: 0.00356903
+16.01.2024 10:13:15 - Res. OME: 0.00698251
+16.01.2024 10:13:15 - Res. xCG: 0.00201914
+16.01.2024 10:13:15 - Res. Missionfuel: 0.000625691
+16.01.2024 10:13:15 - * Trim: CM (current) = 0.059647 | i_Tailplane (new) = -1.26383
+16.01.2024 10:13:15 - ----- Start Iteration: 4 -----
+16.01.2024 10:13:15 - Start : createMissionXML
+16.01.2024 10:13:15 - Start : wingDesign
+16.01.2024 10:13:16 - Start : empennageSizing
+16.01.2024 10:13:16 - Start : engineSizing
+16.01.2024 10:13:16 - Start : propulsionIntegration
+16.01.2024 10:13:16 - Start : landingGearDesign
+16.01.2024 10:13:16 - Start : calculatePolar
+16.01.2024 10:13:22 - Start : massEstimation
+16.01.2024 10:13:22 - Start : systemsDesign
+16.01.2024 10:13:22 - Start : missionAnalysis
+16.01.2024 10:13:47 - * residuals (rel. error):
+16.01.2024 10:13:47 - Res. MTOM: 0.0029715
+16.01.2024 10:13:47 - Res. OME: 0.0019107
+16.01.2024 10:13:47 - Res. xCG: 0.00153079
+16.01.2024 10:13:47 - Res. Missionfuel: 0.00782532
+16.01.2024 10:13:47 - * Trim: CM (current) = -0.000108733 | i_Tailplane (new) = -1.26517
+16.01.2024 10:13:47 - ----- Start Iteration: 5 -----
+16.01.2024 10:13:47 - Start : createMissionXML
+16.01.2024 10:13:47 - Start : wingDesign
+16.01.2024 10:13:48 - Start : empennageSizing
+16.01.2024 10:13:48 - Start : engineSizing
+16.01.2024 10:13:48 - Start : propulsionIntegration
+16.01.2024 10:13:48 - Start : landingGearDesign
+16.01.2024 10:13:48 - Start : calculatePolar
+16.01.2024 10:13:54 - Start : massEstimation
+16.01.2024 10:13:54 - Start : systemsDesign
+16.01.2024 10:13:54 - Start : missionAnalysis
+16.01.2024 10:14:19 - * residuals (rel. error):
+16.01.2024 10:14:19 - Res. MTOM: 0.00157315
+16.01.2024 10:14:19 - Res. OME: 0.00169839
+16.01.2024 10:14:19 - Res. xCG: 0.00109458
+16.01.2024 10:14:19 - Res. Missionfuel: 0.0026738
+16.01.2024 10:14:19 - * Trim: CM (current) = -0.000964752 | i_Tailplane (new) = -1.26366
+16.01.2024 10:14:19 - ----- Start Iteration: 6 -----
+16.01.2024 10:14:19 - Start : createMissionXML
+16.01.2024 10:14:19 - Start : wingDesign
+16.01.2024 10:14:20 - Start : empennageSizing
+16.01.2024 10:14:20 - Start : engineSizing
+16.01.2024 10:14:20 - Start : propulsionIntegration
+16.01.2024 10:14:20 - Start : landingGearDesign
+16.01.2024 10:14:21 - Start : calculatePolar
+16.01.2024 10:14:26 - Start : massEstimation
+16.01.2024 10:14:26 - Start : systemsDesign
+16.01.2024 10:14:27 - Start : missionAnalysis
+16.01.2024 10:14:53 - * residuals (rel. error):
+16.01.2024 10:14:53 - Res. MTOM: 0.000702259
+16.01.2024 10:14:53 - Res. OME: 0.000880019
+16.01.2024 10:14:53 - Res. xCG: 0.000645802
+16.01.2024 10:14:53 - Res. Missionfuel: 0.00093294
+16.01.2024 10:14:53 - * Trim: CM (current) = 8.61659e-005 | i_Tailplane (new) = -1.26373
+16.01.2024 10:14:53 - Trim successful (current CM =8.61659e-005)!
+16.01.2024 10:14:53 - ----- Start Iteration: 7 -----
+16.01.2024 10:14:53 - Start : createMissionXML
+16.01.2024 10:14:53 - Start : wingDesign
+16.01.2024 10:14:53 - Start : empennageSizing
+16.01.2024 10:14:54 - Start : engineSizing
+16.01.2024 10:14:54 - Start : propulsionIntegration
+16.01.2024 10:14:54 - Start : landingGearDesign
+16.01.2024 10:14:54 - Start : calculatePolar
+16.01.2024 10:15:00 - Start : massEstimation
+16.01.2024 10:15:00 - Start : systemsDesign
+16.01.2024 10:15:00 - Start : missionAnalysis
+16.01.2024 10:15:26 - * residuals (rel. error):
+16.01.2024 10:15:26 - Res. MTOM: 0.000351166
+16.01.2024 10:15:26 - Res. OME: 0.000396899
+16.01.2024 10:15:26 - Res. xCG: 0.000403864
+16.01.2024 10:15:26 - Res. Missionfuel: 0.000559207
+16.01.2024 10:15:26 - WARNING: After successful trimming, again deviation in the CM (current CM=0.000155396)!
+16.01.2024 10:15:26 - ----- Start Iteration: 8 -----
+16.01.2024 10:15:26 - Start : createMissionXML
+16.01.2024 10:15:26 - Start : wingDesign
+16.01.2024 10:15:26 - Start : empennageSizing
+16.01.2024 10:15:26 - Start : engineSizing
+16.01.2024 10:15:27 - Start : propulsionIntegration
+16.01.2024 10:15:27 - Start : landingGearDesign
+16.01.2024 10:15:27 - Start : calculatePolar
+16.01.2024 10:15:33 - Start : massEstimation
+16.01.2024 10:15:33 - Start : systemsDesign
+16.01.2024 10:15:33 - Start : missionAnalysis
+16.01.2024 10:15:59 - * residuals (rel. error):
+16.01.2024 10:15:59 - Res. MTOM: 0.000178828
+16.01.2024 10:15:59 - Res. OME: 0.000203046
+16.01.2024 10:15:59 - Res. xCG: 0.000251958
+16.01.2024 10:15:59 - Res. Missionfuel: 0.000282779
+16.01.2024 10:15:59 - WARNING: After successful trimming, again deviation in the CM (current CM=0.000180919)!
+16.01.2024 10:15:59 - ----- Start Iteration: 9 -----
+16.01.2024 10:15:59 - Start : createMissionXML
+16.01.2024 10:15:59 - Start : wingDesign
+16.01.2024 10:15:59 - Start : empennageSizing
+16.01.2024 10:15:59 - Start : engineSizing
+16.01.2024 10:16:00 - Start : propulsionIntegration
+16.01.2024 10:16:00 - Start : landingGearDesign
+16.01.2024 10:16:00 - Start : calculatePolar
+16.01.2024 10:16:06 - Start : massEstimation
+16.01.2024 10:16:06 - Start : systemsDesign
+16.01.2024 10:16:06 - Start : missionAnalysis
+16.01.2024 10:16:31 - * residuals (rel. error):
+16.01.2024 10:16:31 - Res. MTOM: 0.000167934
+16.01.2024 10:16:31 - Res. OME: 0.000105017
+16.01.2024 10:16:31 - Res. xCG: 0.000153745
+16.01.2024 10:16:31 - Res. Missionfuel: 0.00044945
+16.01.2024 10:16:31 - WARNING: After successful trimming, again deviation in the CM (current CM=-0.000825763)!
+16.01.2024 10:16:31 - ----- Start Iteration: 10 -----
+16.01.2024 10:16:31 - Start : createMissionXML
+16.01.2024 10:16:31 - Start : wingDesign
+16.01.2024 10:16:32 - Start : empennageSizing
+16.01.2024 10:16:32 - Start : engineSizing
+16.01.2024 10:16:32 - Start : propulsionIntegration
+16.01.2024 10:16:32 - Start : landingGearDesign
+16.01.2024 10:16:32 - Start : calculatePolar
+16.01.2024 10:16:38 - Start : massEstimation
+16.01.2024 10:16:38 - Start : systemsDesign
+16.01.2024 10:16:38 - Start : missionAnalysis
+16.01.2024 10:17:05 - * residuals (rel. error):
+16.01.2024 10:17:05 - Res. MTOM: 1.03467e-005
+16.01.2024 10:17:05 - Res. OME: 9.78502e-005
+16.01.2024 10:17:05 - Res. xCG: 9.35948e-005
+16.01.2024 10:17:05 - Res. Missionfuel: 0.000168406
+16.01.2024 10:17:05 - WARNING: After successful trimming, again deviation in the CM (current CM=0.000203982)!
+16.01.2024 10:17:05 - ----- Start Iteration: 11 -----
+16.01.2024 10:17:05 - Start : createMissionXML
+16.01.2024 10:17:05 - Start : wingDesign
+16.01.2024 10:17:05 - Start : empennageSizing
+16.01.2024 10:17:05 - Start : engineSizing
+16.01.2024 10:17:06 - Start : propulsionIntegration
+16.01.2024 10:17:06 - Start : landingGearDesign
+16.01.2024 10:17:06 - Start : calculatePolar
+16.01.2024 10:17:12 - Start : massEstimation
+16.01.2024 10:17:12 - Start : systemsDesign
+16.01.2024 10:17:12 - Start : missionAnalysis
+16.01.2024 10:17:38 - * residuals (rel. error):
+16.01.2024 10:17:38 - Res. MTOM: 8.40089e-005
+16.01.2024 10:17:38 - Res. OME: 6.42921e-006
+16.01.2024 10:17:38 - Res. xCG: 5.43163e-005
+16.01.2024 10:17:38 - Res. Missionfuel: 0.000323823
+16.01.2024 10:17:38 - WARNING: After successful trimming, again deviation in the CM (current CM=-0.000817023)!
+16.01.2024 10:17:38 - ----- Start Iteration: 12 -----
+16.01.2024 10:17:38 - Start : createMissionXML
+16.01.2024 10:17:38 - Start : wingDesign
+16.01.2024 10:17:38 - Start : empennageSizing
+16.01.2024 10:17:38 - Start : engineSizing
+16.01.2024 10:17:38 - Start : propulsionIntegration
+16.01.2024 10:17:39 - Start : landingGearDesign
+16.01.2024 10:17:39 - Start : calculatePolar
+16.01.2024 10:17:44 - Start : massEstimation
+16.01.2024 10:17:45 - Start : systemsDesign
+16.01.2024 10:17:45 - Start : missionAnalysis
+16.01.2024 10:18:10 - * residuals (rel. error):
+16.01.2024 10:18:10 - Res. MTOM: 4.17282e-005
+16.01.2024 10:18:10 - Res. OME: 4.96272e-005
+16.01.2024 10:18:10 - Res. xCG: 3.54063e-005
+16.01.2024 10:18:10 - Res. Missionfuel: 6.11689e-005
+16.01.2024 10:18:10 - WARNING: After successful trimming, again deviation in the CM (current CM=-0.000808421)!
+16.01.2024 10:18:10 - Execute final runs (with plots on)!
+16.01.2024 10:18:10 - ----- Start Iteration: 13 -----
+16.01.2024 10:18:10 - Start : createMissionXML
+16.01.2024 10:18:10 - Start : wingDesign
+16.01.2024 10:18:13 - Start : empennageSizing
+16.01.2024 10:18:15 - Start : engineSizing
+16.01.2024 10:18:16 - Start : propulsionIntegration
+16.01.2024 10:18:17 - Start : landingGearDesign
+16.01.2024 10:18:19 - Start : calculatePolar
+16.01.2024 10:18:36 - Start : massEstimation
+16.01.2024 10:18:38 - Start : systemsDesign
+16.01.2024 10:18:45 - Start : missionAnalysis
+16.01.2024 10:19:33 - * residuals (rel. error):
+16.01.2024 10:19:33 - Res. MTOM: 5.54691e-005
+16.01.2024 10:19:33 - Res. OME: 2.32835e-005
+16.01.2024 10:19:33 - Res. xCG: 1.91064e-005
+16.01.2024 10:19:33 - Res. Missionfuel: 0.00027284
+16.01.2024 10:19:33 - WARNING: After successful trimming, again deviation in the CM (current CM=0.000211352)!
+16.01.2024 10:19:33 - ----- Start Iteration: 14 -----
+16.01.2024 10:19:33 - Start : createMissionXML
+16.01.2024 10:19:34 - Start : wingDesign
+16.01.2024 10:19:36 - Start : empennageSizing
+16.01.2024 10:19:38 - Start : engineSizing
+16.01.2024 10:19:39 - Start : propulsionIntegration
+16.01.2024 10:19:40 - Start : landingGearDesign
+16.01.2024 10:19:42 - Start : calculatePolar
+16.01.2024 10:20:00 - Start : massEstimation
+16.01.2024 10:20:01 - Start : systemsDesign
+16.01.2024 10:20:09 - Start : missionAnalysis
+16.01.2024 10:20:59 - * residuals (rel. error):
+16.01.2024 10:20:59 - Res. MTOM: 2.61546e-005
+16.01.2024 10:20:59 - Res. OME: 3.12678e-005
+16.01.2024 10:20:59 - Res. xCG: 1.15398e-005
+16.01.2024 10:20:59 - Res. Missionfuel: 3.79996e-005
+16.01.2024 10:20:59 - WARNING: After successful trimming, again deviation in the CM (current CM=0.000201467)!
+16.01.2024 10:20:59 -
+16.01.2024 10:20:59 - Convergence! Iteration successfully completed!
+16.01.2024 10:20:59 -
+16.01.2024 10:20:59 - Result of the trim:
+16.01.2024 10:20:59 - Angle of incidence Tailplane: -1.26373deg
+16.01.2024 10:20:59 - CM at optimal Cruise-CL: 0.000201467
+
+16.01.2024 10:20:59 - Iteration 0 (start): MTOM: 83192 | OME: 50088.4 | MF: 0 | xCG_aft: 0
+16.01.2024 10:20:59 - Iteration 1: MTOM: 80388.2 | OME: 43162.8 | MF: 20331.9 | xCG_aft: 17.0953
+16.01.2024 10:20:59 - Iteration 2: MTOM: 79374.8 | OME: 42675.7 | MF: 19802.1 | xCG_aft: 16.9963
+16.01.2024 10:20:59 - Iteration 3: MTOM: 79092.5 | OME: 42379.8 | MF: 19814.5 | xCG_aft: 16.9621
+16.01.2024 10:20:59 - Iteration 4: MTOM: 78858.2 | OME: 42299 | MF: 19660.6 | xCG_aft: 16.9361
+16.01.2024 10:20:59 - Iteration 5: MTOM: 78734.3 | OME: 42227.3 | MF: 19608.2 | xCG_aft: 16.9176
+16.01.2024 10:20:59 - Iteration 6: MTOM: 78679.1 | OME: 42190.1 | MF: 19589.9 | xCG_aft: 16.9067
+16.01.2024 10:20:59 - Iteration 7: MTOM: 78651.5 | OME: 42173.4 | MF: 19579 | xCG_aft: 16.8999
+16.01.2024 10:20:59 - Iteration 8: MTOM: 78637.4 | OME: 42164.8 | MF: 19573.5 | xCG_aft: 16.8956
+16.01.2024 10:20:59 - Iteration 9: MTOM: 78624.2 | OME: 42160.4 | MF: 19564.7 | xCG_aft: 16.893
+16.01.2024 10:20:59 - Iteration 10: MTOM: 78623.4 | OME: 42156.3 | MF: 19568 | xCG_aft: 16.8914
+16.01.2024 10:20:59 - Iteration 11: MTOM: 78616.8 | OME: 42156 | MF: 19561.6 | xCG_aft: 16.8905
+16.01.2024 10:20:59 - Iteration 12: MTOM: 78613.5 | OME: 42153.9 | MF: 19560.4 | xCG_aft: 16.8899
+16.01.2024 10:20:59 - Iteration 13: MTOM: 78617.8 | OME: 42153 | MF: 19565.8 | xCG_aft: 16.8896
+16.01.2024 10:20:59 - Iteration 14: MTOM: 78619.9 | OME: 42154.3 | MF: 19566.5 | xCG_aft: 16.8894
+
+16.01.2024 10:20:59 - ---------------------------------------------
+16.01.2024 10:20:59 - Analysis of the Study Mission ...
+16.01.2024 10:20:59 - * Check switches for study mission...
+16.01.2024 10:20:59 - --- Start Study Mission Iteration: 1 ---
+16.01.2024 10:20:59 - Start : createMissionXML
+16.01.2024 10:20:59 - Start : systemsDesign
+16.01.2024 10:21:05 - Start : missionAnalysis
+16.01.2024 10:21:43 - --- Start Study Mission Iteration: 2 ---
+16.01.2024 10:21:43 - Start : createMissionXML
+16.01.2024 10:21:43 - Start : systemsDesign
+16.01.2024 10:21:50 - Start : missionAnalysis
+16.01.2024 10:22:20 - --- Study Mission: Residuals (relative error) after Iteration 2 ---
+16.01.2024 10:22:20 - Residuum Mission fuel (study mission): 0
+16.01.2024 10:22:20 - Residual flight altitude of the first cruise segment: 0
+16.01.2024 10:22:20 - Residuum Range (study mission): 0
+16.01.2024 10:22:20 - Residuum TOM (study mission): 0
+16.01.2024 10:22:20 - ... Convergence! Iteration of Study Mission successfully completed!
+16.01.2024 10:22:20 -
+16.01.2024 10:22:20 - ----------------------------------------
+16.01.2024 10:22:20 - Postprocessing ...
+16.01.2024 10:22:20 - Start : calculatePerformance
+16.01.2024 10:22:34 - Start : calculateCosts
+16.01.2024 10:22:37 - Start : estimateDOC
+16.01.2024 10:22:38 - Start : calculateCosts
+16.01.2024 10:22:41 - Start : calculateEmissions
+16.01.2024 10:23:09 - Start : reportGenerator
+16.01.2024 10:23:10 - Start : cpacsInterface
+16.01.2024 10:23:11 - Start : designEvaluator
+16.01.2024 10:23:11 - ERROR: Tool-Execution: Error code 1 in Program designEvaluator
+16.01.2024 10:23:11 - ERROR: Errors have occurred in PostProcessing! Error codes of the PostProc tools: [0,0,0,0,0,0,0,1]. Abort program with Special ExitCode 111!
+16.01.2024 10:23:11 - ERROR: Error in Postprocessing steps. Error code: 38145
+
+16.01.2024 10:23:11 - ---------------------------------------------
+16.01.2024 10:23:11 - Checking Requirements ...
+16.01.2024 10:23:11 - * Checking TLARs ...
+16.01.2024 10:23:11 - * Checking tank volume for design ...
+16.01.2024 10:23:11 - * Checking tank volume for study ...
+16.01.2024 10:23:11 - * Checking reserve fuel ...
+16.01.2024 10:23:11 - * Checking TOM on study mission ...
+16.01.2024 10:23:11 - ... No tested TLAR was violated.
+16.01.2024 10:23:11 - ... All existing TLARs were checked and complied with. Good design!
+16.01.2024 10:23:11 - WARNING: Outputs are written, but may contain errors!
+16.01.2024 10:23:11 - ... calculation finished!
+16.01.2024 10:23:11 - Create csvFiles directory at path: csvFiles\
+16.01.2024 10:23:11 - Create pltFiles directory at path: pltFiles\
+16.01.2024 10:23:11 - Write output ...
+16.01.2024 10:23:11 - Create Plots ...
+16.01.2024 10:23:11 - Copy Plotting files ...
+16.01.2024 10:23:11 - Write HTML-Report ...
+16.01.2024 10:23:11 - Needed time: 11.7 min
+16.01.2024 10:23:12 - Finish convergenceLoop
+*******************************************************************************
+21.02.2024 09:55:53 - Start convergenceLoop
+21.02.2024 09:55:53 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+21.02.2024 09:55:53 - Start calculation ...
+21.02.2024 09:55:53 - Design Modus 1: Clean sheet design!
+21.02.2024 09:55:53 - Settings in Sub-Programs will be checked!
+21.02.2024 09:55:53 - * Checking design point:
+21.02.2024 09:55:53 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+21.02.2024 09:55:53 - The in the Setup-Steps selected initialSizing module overwrites them.
+21.02.2024 09:55:53 - ----
+21.02.2024 09:55:53 - * Checking fuselage geometry:
+21.02.2024 09:55:53 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+21.02.2024 09:55:53 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+21.02.2024 09:55:53 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+21.02.2024 09:55:53 - ----
+21.02.2024 09:55:53 - * Checking createMissionXML:
+21.02.2024 09:55:53 - - Design mission will be created.
+21.02.2024 09:55:53 - ----
+21.02.2024 09:55:53 - * Checking wing design:
+21.02.2024 09:55:53 - - Wing geometry available in XML file.
+21.02.2024 09:55:53 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+21.02.2024 09:55:53 - - Existing wing geometry will be overwritten by initialWingSizing module.
+21.02.2024 09:55:53 - ----
+21.02.2024 09:55:53 - * Checking empennage design:
+21.02.2024 09:55:53 - - Tail geometry available in XML file.
+21.02.2024 09:55:53 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+21.02.2024 09:55:53 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+21.02.2024 09:55:53 - ----
+21.02.2024 09:55:53 - * Checking nacelle design and propulsion integration:
+21.02.2024 09:55:53 - - Nacelles already exist.
+21.02.2024 09:55:53 - - Nacelle geometries will be designed by the propulsion integration module.!
+21.02.2024 09:55:53 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+21.02.2024 09:55:53 - ----
+21.02.2024 09:55:53 - * Checking systems design:
+21.02.2024 09:55:53 - - systemsDesign is running in design mode.
+21.02.2024 09:55:53 - ----
+21.02.2024 09:55:53 - * Checking mission analysis:
+21.02.2024 09:55:53 - - missionAnalysis is running in design mode.
+21.02.2024 09:55:53 - ----
+21.02.2024 09:55:53 - * Checking performance calculation:
+21.02.2024 09:55:53 - - Take-off and landing performance are estimated.
+21.02.2024 09:55:53 - - Payload-Range diagram is calculated.
+21.02.2024 09:55:53 - ----
+21.02.2024 09:55:53 - Still to be continued? (y/n)
+21.02.2024 09:55:53 - Still to be continued? (y/n)
+21.02.2024 09:55:59 - ----------------------------------------
+21.02.2024 09:55:59 - Setup-Tools ...
+21.02.2024 09:55:59 - Start : initialSizing
+21.02.2024 09:56:00 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+21.02.2024 09:56:00 - ERROR: Error in Setup steps. Error code: 1
+
+21.02.2024 09:56:00 - ---------------------------------------------
+21.02.2024 09:56:00 - Checking Requirements ...
+21.02.2024 09:56:00 - * Checking TLARs ...
+21.02.2024 09:56:00 - * Checking tank volume for design ...
+21.02.2024 09:56:00 - * Checking tank volume for study ...
+21.02.2024 09:56:00 - * Checking reserve fuel ...
+21.02.2024 09:56:00 - * Checking TOM on study mission ...
+21.02.2024 09:56:00 - WARNING: Outputs are written, but may contain errors!
+21.02.2024 09:56:00 - ... calculation finished!
+21.02.2024 09:56:00 - Write output ...
+21.02.2024 09:56:00 - Create Plots ...
+21.02.2024 09:56:00 - Copy Plotting files ...
+21.02.2024 09:56:00 - Write HTML-Report ...
+21.02.2024 09:56:00 - Needed time: 0.116667 min
+21.02.2024 09:56:00 - Finish convergenceLoop
+*******************************************************************************
+21.02.2024 10:02:49 - Start convergenceLoop
+21.02.2024 10:02:49 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+21.02.2024 10:02:49 - Start calculation ...
+21.02.2024 10:02:50 - Design Modus 1: Clean sheet design!
+21.02.2024 10:02:50 - Settings in Sub-Programs will be checked!
+21.02.2024 10:02:50 - * Checking design point:
+21.02.2024 10:02:50 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+21.02.2024 10:02:50 - The in the Setup-Steps selected initialSizing module overwrites them.
+21.02.2024 10:02:50 - ----
+21.02.2024 10:02:50 - * Checking fuselage geometry:
+21.02.2024 10:02:50 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+21.02.2024 10:02:50 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+21.02.2024 10:02:50 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+21.02.2024 10:02:50 - ----
+21.02.2024 10:02:50 - * Checking createMissionXML:
+21.02.2024 10:02:50 - - Design mission will be created.
+21.02.2024 10:02:50 - ----
+21.02.2024 10:02:50 - * Checking wing design:
+21.02.2024 10:02:50 - - Wing geometry available in XML file.
+21.02.2024 10:02:50 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+21.02.2024 10:02:50 - - Existing wing geometry will be overwritten by initialWingSizing module.
+21.02.2024 10:02:50 - ----
+21.02.2024 10:02:50 - * Checking empennage design:
+21.02.2024 10:02:50 - - Tail geometry available in XML file.
+21.02.2024 10:02:50 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+21.02.2024 10:02:50 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+21.02.2024 10:02:50 - ----
+21.02.2024 10:02:50 - * Checking nacelle design and propulsion integration:
+21.02.2024 10:02:50 - - Nacelles already exist.
+21.02.2024 10:02:50 - - Nacelle geometries will be designed by the propulsion integration module.!
+21.02.2024 10:02:50 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+21.02.2024 10:02:50 - ----
+21.02.2024 10:02:50 - * Checking systems design:
+21.02.2024 10:02:50 - - systemsDesign is running in design mode.
+21.02.2024 10:02:50 - ----
+21.02.2024 10:02:50 - * Checking mission analysis:
+21.02.2024 10:02:50 - - missionAnalysis is running in design mode.
+21.02.2024 10:02:50 - ----
+21.02.2024 10:02:50 - * Checking performance calculation:
+21.02.2024 10:02:50 - - Take-off and landing performance are estimated.
+21.02.2024 10:02:50 - - Payload-Range diagram is calculated.
+21.02.2024 10:02:50 - ----
+21.02.2024 10:02:50 - Still to be continued? (y/n)
+21.02.2024 10:02:56 - ----------------------------------------
+21.02.2024 10:02:56 - Setup-Tools ...
+21.02.2024 10:02:56 - Start : initialSizing
+21.02.2024 10:02:57 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+21.02.2024 10:02:57 - ERROR: Error in Setup steps. Error code: 1
+
+21.02.2024 10:02:57 - ---------------------------------------------
+21.02.2024 10:02:57 - Checking Requirements ...
+21.02.2024 10:02:57 - * Checking TLARs ...
+21.02.2024 10:02:57 - * Checking tank volume for design ...
+21.02.2024 10:02:57 - * Checking tank volume for study ...
+21.02.2024 10:02:57 - * Checking reserve fuel ...
+21.02.2024 10:02:57 - * Checking TOM on study mission ...
+21.02.2024 10:02:57 - WARNING: Outputs are written, but may contain errors!
+21.02.2024 10:02:57 - ... calculation finished!
+21.02.2024 10:02:57 - Write output ...
+21.02.2024 10:02:57 - Create Plots ...
+21.02.2024 10:02:57 - Copy Plotting files ...
+21.02.2024 10:02:57 - Write HTML-Report ...
+21.02.2024 10:02:57 - Needed time: 0.133333 min
+21.02.2024 10:02:57 - Finish convergenceLoop
+*******************************************************************************
+21.02.2024 10:33:12 - Start convergenceLoop
+21.02.2024 10:33:12 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+21.02.2024 10:33:12 - Start calculation ...
+21.02.2024 10:33:13 - Design Modus 1: Clean sheet design!
+21.02.2024 10:33:13 - Settings in Sub-Programs will be checked!
+21.02.2024 10:33:13 - * Checking design point:
+21.02.2024 10:33:13 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+21.02.2024 10:33:13 - The in the Setup-Steps selected initialSizing module overwrites them.
+21.02.2024 10:33:13 - ----
+21.02.2024 10:33:13 - * Checking fuselage geometry:
+21.02.2024 10:33:13 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+21.02.2024 10:33:13 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+21.02.2024 10:33:13 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+21.02.2024 10:33:13 - ----
+21.02.2024 10:33:13 - * Checking createMissionXML:
+21.02.2024 10:33:13 - - Design mission will be created.
+21.02.2024 10:33:13 - ----
+21.02.2024 10:33:13 - * Checking wing design:
+21.02.2024 10:33:13 - - Wing geometry available in XML file.
+21.02.2024 10:33:13 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+21.02.2024 10:33:13 - - Existing wing geometry will be overwritten by initialWingSizing module.
+21.02.2024 10:33:13 - ----
+21.02.2024 10:33:13 - * Checking empennage design:
+21.02.2024 10:33:13 - - Tail geometry available in XML file.
+21.02.2024 10:33:13 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+21.02.2024 10:33:13 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+21.02.2024 10:33:13 - ----
+21.02.2024 10:33:13 - * Checking nacelle design and propulsion integration:
+21.02.2024 10:33:13 - - Nacelles already exist.
+21.02.2024 10:33:13 - - Nacelle geometries will be designed by the propulsion integration module.!
+21.02.2024 10:33:13 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+21.02.2024 10:33:13 - ----
+21.02.2024 10:33:13 - * Checking systems design:
+21.02.2024 10:33:13 - - systemsDesign is running in design mode.
+21.02.2024 10:33:13 - ----
+21.02.2024 10:33:13 - * Checking mission analysis:
+21.02.2024 10:33:13 - - missionAnalysis is running in design mode.
+21.02.2024 10:33:13 - ----
+21.02.2024 10:33:13 - * Checking performance calculation:
+21.02.2024 10:33:13 - - Take-off and landing performance are estimated.
+21.02.2024 10:33:13 - - Payload-Range diagram is calculated.
+21.02.2024 10:33:13 - ----
+21.02.2024 10:33:13 - Still to be continued? (y/n)
+21.02.2024 10:33:18 - ----------------------------------------
+21.02.2024 10:33:18 - Setup-Tools ...
+21.02.2024 10:33:18 - Start : initialSizing
+21.02.2024 10:33:18 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+21.02.2024 10:33:18 - ERROR: Error in Setup steps. Error code: 1
+
+21.02.2024 10:33:18 - ---------------------------------------------
+21.02.2024 10:33:18 - Checking Requirements ...
+21.02.2024 10:33:18 - * Checking TLARs ...
+21.02.2024 10:33:18 - * Checking tank volume for design ...
+21.02.2024 10:33:18 - * Checking tank volume for study ...
+21.02.2024 10:33:18 - * Checking reserve fuel ...
+21.02.2024 10:33:18 - * Checking TOM on study mission ...
+21.02.2024 10:33:18 - WARNING: Outputs are written, but may contain errors!
+21.02.2024 10:33:18 - ... calculation finished!
+21.02.2024 10:33:18 - Write output ...
+21.02.2024 10:33:18 - Create Plots ...
+21.02.2024 10:33:18 - Copy Plotting files ...
+21.02.2024 10:33:18 - Write HTML-Report ...
+21.02.2024 10:33:18 - Needed time: 0.1 min
+21.02.2024 10:33:19 - Finish convergenceLoop
+*******************************************************************************
+22.02.2024 13:02:59 - Start convergenceLoop
+22.02.2024 13:02:59 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.02.2024 13:02:59 - Start calculation ...
+22.02.2024 13:02:59 - Design Modus 1: Clean sheet design!
+22.02.2024 13:02:59 - Settings in Sub-Programs will be checked!
+22.02.2024 13:02:59 - * Checking design point:
+22.02.2024 13:02:59 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+22.02.2024 13:02:59 - The in the Setup-Steps selected initialSizing module overwrites them.
+22.02.2024 13:02:59 - ----
+22.02.2024 13:02:59 - * Checking fuselage geometry:
+22.02.2024 13:02:59 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+22.02.2024 13:02:59 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+22.02.2024 13:02:59 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+22.02.2024 13:02:59 - ----
+22.02.2024 13:02:59 - * Checking createMissionXML:
+22.02.2024 13:02:59 - - Design mission will be created.
+22.02.2024 13:02:59 - ----
+22.02.2024 13:02:59 - * Checking wing design:
+22.02.2024 13:02:59 - - Wing geometry available in XML file.
+22.02.2024 13:02:59 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+22.02.2024 13:02:59 - - Existing wing geometry will be overwritten by initialWingSizing module.
+22.02.2024 13:02:59 - ----
+22.02.2024 13:02:59 - * Checking empennage design:
+22.02.2024 13:02:59 - - Tail geometry available in XML file.
+22.02.2024 13:02:59 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+22.02.2024 13:02:59 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+22.02.2024 13:02:59 - ----
+22.02.2024 13:02:59 - * Checking nacelle design and propulsion integration:
+22.02.2024 13:02:59 - - Nacelles already exist.
+22.02.2024 13:02:59 - - Nacelle geometries will be designed by the propulsion integration module.!
+22.02.2024 13:02:59 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+22.02.2024 13:02:59 - ----
+22.02.2024 13:02:59 - * Checking systems design:
+22.02.2024 13:02:59 - - systemsDesign is running in design mode.
+22.02.2024 13:02:59 - ----
+22.02.2024 13:02:59 - * Checking mission analysis:
+22.02.2024 13:02:59 - - missionAnalysis is running in design mode.
+22.02.2024 13:02:59 - ----
+22.02.2024 13:02:59 - * Checking performance calculation:
+22.02.2024 13:02:59 - - Take-off and landing performance are estimated.
+22.02.2024 13:02:59 - - Payload-Range diagram is calculated.
+22.02.2024 13:02:59 - ----
+22.02.2024 13:02:59 - Still to be continued? (y/n)
+22.02.2024 13:02:59 - Still to be continued? (y/n)
+22.02.2024 13:03:14 - ----------------------------------------
+22.02.2024 13:03:14 - Setup-Tools ...
+22.02.2024 13:03:14 - Start : initialSizing
+22.02.2024 13:03:14 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+22.02.2024 13:03:14 - ERROR: Error in Setup steps. Error code: 1
+
+22.02.2024 13:03:14 - ---------------------------------------------
+22.02.2024 13:03:14 - Checking Requirements ...
+22.02.2024 13:03:14 - * Checking TLARs ...
+22.02.2024 13:03:14 - * Checking tank volume for design ...
+22.02.2024 13:03:14 - * Checking tank volume for study ...
+22.02.2024 13:03:14 - * Checking reserve fuel ...
+22.02.2024 13:03:14 - * Checking TOM on study mission ...
+22.02.2024 13:03:14 - WARNING: Outputs are written, but may contain errors!
+22.02.2024 13:03:14 - ... calculation finished!
+22.02.2024 13:03:14 - Write output ...
+22.02.2024 13:03:14 - Create Plots ...
+22.02.2024 13:03:14 - Copy Plotting files ...
+22.02.2024 13:03:14 - Write HTML-Report ...
+22.02.2024 13:03:14 - Needed time: 0.25 min
+22.02.2024 13:03:14 - Finish convergenceLoop
+*******************************************************************************
+22.02.2024 13:03:14 - Start convergenceLoop
+22.02.2024 13:03:14 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.02.2024 13:03:14 - Start calculation ...
+22.02.2024 13:03:15 - Design Modus 1: Clean sheet design!
+22.02.2024 13:03:15 - Settings in Sub-Programs will be checked!
+22.02.2024 13:03:15 - * Checking design point:
+22.02.2024 13:03:15 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+22.02.2024 13:03:15 - The in the Setup-Steps selected initialSizing module overwrites them.
+22.02.2024 13:03:15 - ----
+22.02.2024 13:03:15 - * Checking fuselage geometry:
+22.02.2024 13:03:15 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+22.02.2024 13:03:15 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+22.02.2024 13:03:15 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+22.02.2024 13:03:15 - ----
+22.02.2024 13:03:15 - * Checking createMissionXML:
+22.02.2024 13:03:15 - - Design mission will be created.
+22.02.2024 13:03:15 - ----
+22.02.2024 13:03:15 - * Checking wing design:
+22.02.2024 13:03:15 - - Wing geometry available in XML file.
+22.02.2024 13:03:15 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+22.02.2024 13:03:15 - - Existing wing geometry will be overwritten by initialWingSizing module.
+22.02.2024 13:03:15 - ----
+22.02.2024 13:03:15 - * Checking empennage design:
+22.02.2024 13:03:15 - - Tail geometry available in XML file.
+22.02.2024 13:03:15 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+22.02.2024 13:03:15 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+22.02.2024 13:03:15 - ----
+22.02.2024 13:03:15 - * Checking nacelle design and propulsion integration:
+22.02.2024 13:03:15 - - Nacelles already exist.
+22.02.2024 13:03:15 - - Nacelle geometries will be designed by the propulsion integration module.!
+22.02.2024 13:03:15 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+22.02.2024 13:03:15 - ----
+22.02.2024 13:03:15 - * Checking systems design:
+22.02.2024 13:03:15 - - systemsDesign is running in design mode.
+22.02.2024 13:03:15 - ----
+22.02.2024 13:03:15 - * Checking mission analysis:
+22.02.2024 13:03:15 - - missionAnalysis is running in design mode.
+22.02.2024 13:03:15 - ----
+22.02.2024 13:03:15 - * Checking performance calculation:
+22.02.2024 13:03:15 - - Take-off and landing performance are estimated.
+22.02.2024 13:03:15 - - Payload-Range diagram is calculated.
+22.02.2024 13:03:15 - ----
+22.02.2024 13:03:15 - Still to be continued? (y/n)
+22.02.2024 13:03:18 - ----------------------------------------
+22.02.2024 13:03:18 - Setup-Tools ...
+22.02.2024 13:03:18 - Start : initialSizing
+22.02.2024 13:03:19 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+22.02.2024 13:03:19 - ERROR: Error in Setup steps. Error code: 1
+
+22.02.2024 13:03:19 - ---------------------------------------------
+22.02.2024 13:03:19 - Checking Requirements ...
+22.02.2024 13:03:19 - * Checking TLARs ...
+22.02.2024 13:03:19 - * Checking tank volume for design ...
+22.02.2024 13:03:19 - * Checking tank volume for study ...
+22.02.2024 13:03:19 - * Checking reserve fuel ...
+22.02.2024 13:03:19 - * Checking TOM on study mission ...
+22.02.2024 13:03:19 - WARNING: Outputs are written, but may contain errors!
+22.02.2024 13:03:19 - ... calculation finished!
+22.02.2024 13:03:19 - Write output ...
+22.02.2024 13:03:19 - Create Plots ...
+22.02.2024 13:03:19 - Copy Plotting files ...
+22.02.2024 13:03:19 - Write HTML-Report ...
+22.02.2024 13:03:19 - Needed time: 0.0833333 min
+22.02.2024 13:03:19 - Finish convergenceLoop
+*******************************************************************************
+22.02.2024 13:04:10 - Start convergenceLoop
+22.02.2024 13:04:10 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.02.2024 13:04:10 - Start calculation ...
+22.02.2024 13:04:10 - Design Modus 1: Clean sheet design!
+22.02.2024 13:04:10 - Settings in Sub-Programs will be checked!
+22.02.2024 13:04:10 - * Checking design point:
+22.02.2024 13:04:10 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+22.02.2024 13:04:10 - The in the Setup-Steps selected initialSizing module overwrites them.
+22.02.2024 13:04:10 - ----
+22.02.2024 13:04:10 - * Checking fuselage geometry:
+22.02.2024 13:04:10 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+22.02.2024 13:04:10 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+22.02.2024 13:04:10 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+22.02.2024 13:04:10 - ----
+22.02.2024 13:04:10 - * Checking createMissionXML:
+22.02.2024 13:04:10 - - Design mission will be created.
+22.02.2024 13:04:10 - ----
+22.02.2024 13:04:10 - * Checking wing design:
+22.02.2024 13:04:10 - - Wing geometry available in XML file.
+22.02.2024 13:04:10 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+22.02.2024 13:04:10 - - Existing wing geometry will be overwritten by initialWingSizing module.
+22.02.2024 13:04:10 - ----
+22.02.2024 13:04:10 - * Checking empennage design:
+22.02.2024 13:04:10 - - Tail geometry available in XML file.
+22.02.2024 13:04:10 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+22.02.2024 13:04:10 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+22.02.2024 13:04:10 - ----
+22.02.2024 13:04:10 - * Checking nacelle design and propulsion integration:
+22.02.2024 13:04:10 - - Nacelles already exist.
+22.02.2024 13:04:10 - - Nacelle geometries will be designed by the propulsion integration module.!
+22.02.2024 13:04:10 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+22.02.2024 13:04:10 - ----
+22.02.2024 13:04:10 - * Checking systems design:
+22.02.2024 13:04:10 - - systemsDesign is running in design mode.
+22.02.2024 13:04:10 - ----
+22.02.2024 13:04:10 - * Checking mission analysis:
+22.02.2024 13:04:10 - - missionAnalysis is running in design mode.
+22.02.2024 13:04:10 - ----
+22.02.2024 13:04:10 - * Checking performance calculation:
+22.02.2024 13:04:10 - - Take-off and landing performance are estimated.
+22.02.2024 13:04:10 - - Payload-Range diagram is calculated.
+22.02.2024 13:04:10 - ----
+22.02.2024 13:04:10 - Still to be continued? (y/n)
+22.02.2024 13:04:21 - ----------------------------------------
+22.02.2024 13:04:21 - Setup-Tools ...
+22.02.2024 13:04:21 - Start : initialSizing
+22.02.2024 13:04:21 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+22.02.2024 13:04:21 - ERROR: Error in Setup steps. Error code: 1
+
+22.02.2024 13:04:21 - ---------------------------------------------
+22.02.2024 13:04:21 - Checking Requirements ...
+22.02.2024 13:04:21 - * Checking TLARs ...
+22.02.2024 13:04:21 - * Checking tank volume for design ...
+22.02.2024 13:04:21 - * Checking tank volume for study ...
+22.02.2024 13:04:21 - * Checking reserve fuel ...
+22.02.2024 13:04:21 - * Checking TOM on study mission ...
+22.02.2024 13:04:21 - WARNING: Outputs are written, but may contain errors!
+22.02.2024 13:04:21 - ... calculation finished!
+22.02.2024 13:04:21 - Write output ...
+22.02.2024 13:04:21 - Create Plots ...
+22.02.2024 13:04:21 - Copy Plotting files ...
+22.02.2024 13:04:21 - Write HTML-Report ...
+22.02.2024 13:04:21 - Needed time: 0.183333 min
+22.02.2024 13:04:21 - Finish convergenceLoop
+*******************************************************************************
+22.02.2024 13:04:21 - Start convergenceLoop
+22.02.2024 13:04:21 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.02.2024 13:04:21 - Start calculation ...
+22.02.2024 13:04:22 - Design Modus 1: Clean sheet design!
+22.02.2024 13:04:22 - Settings in Sub-Programs will be checked!
+22.02.2024 13:04:22 - * Checking design point:
+22.02.2024 13:04:22 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+22.02.2024 13:04:22 - The in the Setup-Steps selected initialSizing module overwrites them.
+22.02.2024 13:04:22 - ----
+22.02.2024 13:04:22 - * Checking fuselage geometry:
+22.02.2024 13:04:22 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+22.02.2024 13:04:22 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+22.02.2024 13:04:22 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+22.02.2024 13:04:22 - ----
+22.02.2024 13:04:22 - * Checking createMissionXML:
+22.02.2024 13:04:22 - - Design mission will be created.
+22.02.2024 13:04:22 - ----
+22.02.2024 13:04:22 - * Checking wing design:
+22.02.2024 13:04:22 - - Wing geometry available in XML file.
+22.02.2024 13:04:22 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+22.02.2024 13:04:22 - - Existing wing geometry will be overwritten by initialWingSizing module.
+22.02.2024 13:04:22 - ----
+22.02.2024 13:04:22 - * Checking empennage design:
+22.02.2024 13:04:22 - - Tail geometry available in XML file.
+22.02.2024 13:04:22 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+22.02.2024 13:04:22 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+22.02.2024 13:04:22 - ----
+22.02.2024 13:04:22 - * Checking nacelle design and propulsion integration:
+22.02.2024 13:04:22 - - Nacelles already exist.
+22.02.2024 13:04:22 - - Nacelle geometries will be designed by the propulsion integration module.!
+22.02.2024 13:04:22 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+22.02.2024 13:04:22 - ----
+22.02.2024 13:04:22 - * Checking systems design:
+22.02.2024 13:04:22 - - systemsDesign is running in design mode.
+22.02.2024 13:04:22 - ----
+22.02.2024 13:04:22 - * Checking mission analysis:
+22.02.2024 13:04:22 - - missionAnalysis is running in design mode.
+22.02.2024 13:04:22 - ----
+22.02.2024 13:04:22 - * Checking performance calculation:
+22.02.2024 13:04:22 - - Take-off and landing performance are estimated.
+22.02.2024 13:04:22 - - Payload-Range diagram is calculated.
+22.02.2024 13:04:22 - ----
+22.02.2024 13:04:22 - Still to be continued? (y/n)
+22.02.2024 13:04:25 - ----------------------------------------
+22.02.2024 13:04:25 - Setup-Tools ...
+22.02.2024 13:04:25 - Start : initialSizing
+22.02.2024 13:04:25 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+22.02.2024 13:04:25 - ERROR: Error in Setup steps. Error code: 1
+
+22.02.2024 13:04:25 - ---------------------------------------------
+22.02.2024 13:04:25 - Checking Requirements ...
+22.02.2024 13:04:25 - * Checking TLARs ...
+22.02.2024 13:04:25 - * Checking tank volume for design ...
+22.02.2024 13:04:25 - * Checking tank volume for study ...
+22.02.2024 13:04:25 - * Checking reserve fuel ...
+22.02.2024 13:04:25 - * Checking TOM on study mission ...
+22.02.2024 13:04:25 - WARNING: Outputs are written, but may contain errors!
+22.02.2024 13:04:25 - ... calculation finished!
+22.02.2024 13:04:25 - Write output ...
+22.02.2024 13:04:25 - Create Plots ...
+22.02.2024 13:04:25 - Copy Plotting files ...
+22.02.2024 13:04:25 - Write HTML-Report ...
+22.02.2024 13:04:25 - Needed time: 0.0666667 min
+22.02.2024 13:04:25 - Finish convergenceLoop
+*******************************************************************************
+22.02.2024 13:04:32 - Start convergenceLoop
+22.02.2024 13:04:32 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.02.2024 13:04:32 - Start calculation ...
+22.02.2024 13:04:33 - Design Modus 1: Clean sheet design!
+22.02.2024 13:04:33 - Settings in Sub-Programs will be checked!
+22.02.2024 13:04:33 - * Checking design point:
+22.02.2024 13:04:33 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+22.02.2024 13:04:33 - The in the Setup-Steps selected initialSizing module overwrites them.
+22.02.2024 13:04:33 - ----
+22.02.2024 13:04:33 - * Checking fuselage geometry:
+22.02.2024 13:04:33 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+22.02.2024 13:04:33 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+22.02.2024 13:04:33 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+22.02.2024 13:04:33 - ----
+22.02.2024 13:04:33 - * Checking createMissionXML:
+22.02.2024 13:04:33 - - Design mission will be created.
+22.02.2024 13:04:33 - ----
+22.02.2024 13:04:33 - * Checking wing design:
+22.02.2024 13:04:33 - - Wing geometry available in XML file.
+22.02.2024 13:04:33 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+22.02.2024 13:04:33 - - Existing wing geometry will be overwritten by initialWingSizing module.
+22.02.2024 13:04:33 - ----
+22.02.2024 13:04:33 - * Checking empennage design:
+22.02.2024 13:04:33 - - Tail geometry available in XML file.
+22.02.2024 13:04:33 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+22.02.2024 13:04:33 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+22.02.2024 13:04:33 - ----
+22.02.2024 13:04:33 - * Checking nacelle design and propulsion integration:
+22.02.2024 13:04:33 - - Nacelles already exist.
+22.02.2024 13:04:33 - - Nacelle geometries will be designed by the propulsion integration module.!
+22.02.2024 13:04:33 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+22.02.2024 13:04:33 - ----
+22.02.2024 13:04:33 - * Checking systems design:
+22.02.2024 13:04:33 - - systemsDesign is running in design mode.
+22.02.2024 13:04:33 - ----
+22.02.2024 13:04:33 - * Checking mission analysis:
+22.02.2024 13:04:33 - - missionAnalysis is running in design mode.
+22.02.2024 13:04:33 - ----
+22.02.2024 13:04:33 - * Checking performance calculation:
+22.02.2024 13:04:33 - - Take-off and landing performance are estimated.
+22.02.2024 13:04:33 - - Payload-Range diagram is calculated.
+22.02.2024 13:04:33 - ----
+22.02.2024 13:04:33 - Still to be continued? (y/n)
+22.02.2024 13:06:02 - ----------------------------------------
+22.02.2024 13:06:02 - Setup-Tools ...
+22.02.2024 13:06:02 - Start : initialSizing
+22.02.2024 13:06:02 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+22.02.2024 13:06:02 - ERROR: Error in Setup steps. Error code: 1
+
+22.02.2024 13:06:02 - ---------------------------------------------
+22.02.2024 13:06:02 - Checking Requirements ...
+22.02.2024 13:06:02 - * Checking TLARs ...
+22.02.2024 13:06:02 - * Checking tank volume for design ...
+22.02.2024 13:06:02 - * Checking tank volume for study ...
+22.02.2024 13:06:02 - * Checking reserve fuel ...
+22.02.2024 13:06:02 - * Checking TOM on study mission ...
+22.02.2024 13:06:02 - WARNING: Outputs are written, but may contain errors!
+22.02.2024 13:06:02 - ... calculation finished!
+22.02.2024 13:06:02 - Write output ...
+22.02.2024 13:06:02 - Create Plots ...
+22.02.2024 13:06:02 - Copy Plotting files ...
+22.02.2024 13:06:02 - Write HTML-Report ...
+22.02.2024 13:06:02 - Needed time: 1.5 min
+22.02.2024 13:06:02 - Finish convergenceLoop
+*******************************************************************************
+22.02.2024 13:06:03 - Start convergenceLoop
+22.02.2024 13:06:03 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.02.2024 13:06:03 - Start calculation ...
+22.02.2024 13:06:03 - Design Modus 1: Clean sheet design!
+22.02.2024 13:06:03 - Settings in Sub-Programs will be checked!
+22.02.2024 13:06:03 - * Checking design point:
+22.02.2024 13:06:03 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+22.02.2024 13:06:03 - The in the Setup-Steps selected initialSizing module overwrites them.
+22.02.2024 13:06:03 - ----
+22.02.2024 13:06:03 - * Checking fuselage geometry:
+22.02.2024 13:06:03 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+22.02.2024 13:06:03 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+22.02.2024 13:06:03 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+22.02.2024 13:06:03 - ----
+22.02.2024 13:06:03 - * Checking createMissionXML:
+22.02.2024 13:06:03 - - Design mission will be created.
+22.02.2024 13:06:03 - ----
+22.02.2024 13:06:03 - * Checking wing design:
+22.02.2024 13:06:03 - - Wing geometry available in XML file.
+22.02.2024 13:06:03 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+22.02.2024 13:06:03 - - Existing wing geometry will be overwritten by initialWingSizing module.
+22.02.2024 13:06:03 - ----
+22.02.2024 13:06:03 - * Checking empennage design:
+22.02.2024 13:06:03 - - Tail geometry available in XML file.
+22.02.2024 13:06:03 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+22.02.2024 13:06:03 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+22.02.2024 13:06:03 - ----
+22.02.2024 13:06:03 - * Checking nacelle design and propulsion integration:
+22.02.2024 13:06:03 - - Nacelles already exist.
+22.02.2024 13:06:03 - - Nacelle geometries will be designed by the propulsion integration module.!
+22.02.2024 13:06:03 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+22.02.2024 13:06:03 - ----
+22.02.2024 13:06:03 - * Checking systems design:
+22.02.2024 13:06:03 - - systemsDesign is running in design mode.
+22.02.2024 13:06:03 - ----
+22.02.2024 13:06:03 - * Checking mission analysis:
+22.02.2024 13:06:03 - - missionAnalysis is running in design mode.
+22.02.2024 13:06:03 - ----
+22.02.2024 13:06:03 - * Checking performance calculation:
+22.02.2024 13:06:03 - - Take-off and landing performance are estimated.
+22.02.2024 13:06:03 - - Payload-Range diagram is calculated.
+22.02.2024 13:06:03 - ----
+22.02.2024 13:06:03 - Still to be continued? (y/n)
+22.02.2024 13:06:05 - ----------------------------------------
+22.02.2024 13:06:05 - Setup-Tools ...
+22.02.2024 13:06:05 - Start : initialSizing
+22.02.2024 13:06:05 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+22.02.2024 13:06:05 - ERROR: Error in Setup steps. Error code: 1
+
+22.02.2024 13:06:05 - ---------------------------------------------
+22.02.2024 13:06:05 - Checking Requirements ...
+22.02.2024 13:06:05 - * Checking TLARs ...
+22.02.2024 13:06:05 - * Checking tank volume for design ...
+22.02.2024 13:06:05 - * Checking tank volume for study ...
+22.02.2024 13:06:05 - * Checking reserve fuel ...
+22.02.2024 13:06:05 - * Checking TOM on study mission ...
+22.02.2024 13:06:05 - WARNING: Outputs are written, but may contain errors!
+22.02.2024 13:06:05 - ... calculation finished!
+22.02.2024 13:06:05 - Write output ...
+22.02.2024 13:06:05 - Create Plots ...
+22.02.2024 13:06:05 - Copy Plotting files ...
+22.02.2024 13:06:05 - Write HTML-Report ...
+22.02.2024 13:06:05 - Needed time: 0.0333333 min
+22.02.2024 13:06:05 - Finish convergenceLoop
+*******************************************************************************
+22.02.2024 13:17:23 - Start convergenceLoop
+22.02.2024 13:17:23 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.02.2024 13:17:23 - Start calculation ...
+22.02.2024 13:17:23 - Design Modus 1: Clean sheet design!
+22.02.2024 13:17:23 - Settings in Sub-Programs will be checked!
+22.02.2024 13:17:23 - * Checking design point:
+22.02.2024 13:17:23 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+22.02.2024 13:17:23 - The in the Setup-Steps selected initialSizing module overwrites them.
+22.02.2024 13:17:23 - ----
+22.02.2024 13:17:23 - * Checking fuselage geometry:
+22.02.2024 13:17:23 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+22.02.2024 13:17:23 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+22.02.2024 13:17:23 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+22.02.2024 13:17:23 - ----
+22.02.2024 13:17:23 - * Checking createMissionXML:
+22.02.2024 13:17:23 - - Design mission will be created.
+22.02.2024 13:17:23 - ----
+22.02.2024 13:17:23 - * Checking wing design:
+22.02.2024 13:17:23 - - Wing geometry available in XML file.
+22.02.2024 13:17:23 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+22.02.2024 13:17:23 - - Existing wing geometry will be overwritten by initialWingSizing module.
+22.02.2024 13:17:23 - ----
+22.02.2024 13:17:23 - * Checking empennage design:
+22.02.2024 13:17:23 - - Tail geometry available in XML file.
+22.02.2024 13:17:23 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+22.02.2024 13:17:23 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+22.02.2024 13:17:23 - ----
+22.02.2024 13:17:23 - * Checking nacelle design and propulsion integration:
+22.02.2024 13:17:23 - - Nacelles already exist.
+22.02.2024 13:17:23 - - Nacelle geometries will be designed by the propulsion integration module.!
+22.02.2024 13:17:23 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+22.02.2024 13:17:23 - ----
+22.02.2024 13:17:23 - * Checking systems design:
+22.02.2024 13:17:23 - - systemsDesign is running in design mode.
+22.02.2024 13:17:23 - ----
+22.02.2024 13:17:23 - * Checking mission analysis:
+22.02.2024 13:17:23 - - missionAnalysis is running in design mode.
+22.02.2024 13:17:23 - ----
+22.02.2024 13:17:23 - * Checking performance calculation:
+22.02.2024 13:17:23 - - Take-off and landing performance are estimated.
+22.02.2024 13:17:23 - - Payload-Range diagram is calculated.
+22.02.2024 13:17:23 - ----
+22.02.2024 13:17:23 - Still to be continued? (y/n)
+22.02.2024 13:17:27 - ----------------------------------------
+22.02.2024 13:17:27 - Setup-Tools ...
+22.02.2024 13:17:27 - Start : initialSizing
+22.02.2024 13:17:27 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+22.02.2024 13:17:27 - ERROR: Error in Setup steps. Error code: 1
+
+22.02.2024 13:17:27 - ---------------------------------------------
+22.02.2024 13:17:27 - Checking Requirements ...
+22.02.2024 13:17:27 - * Checking TLARs ...
+22.02.2024 13:17:27 - * Checking tank volume for design ...
+22.02.2024 13:17:27 - * Checking tank volume for study ...
+22.02.2024 13:17:27 - * Checking reserve fuel ...
+22.02.2024 13:17:27 - * Checking TOM on study mission ...
+22.02.2024 13:17:27 - WARNING: Outputs are written, but may contain errors!
+22.02.2024 13:17:27 - ... calculation finished!
+22.02.2024 13:17:27 - Write output ...
+22.02.2024 13:17:27 - Create Plots ...
+22.02.2024 13:17:27 - Copy Plotting files ...
+22.02.2024 13:17:27 - Write HTML-Report ...
+22.02.2024 13:17:27 - Needed time: 0.0666667 min
+22.02.2024 13:17:28 - Finish convergenceLoop
+*******************************************************************************
+26.02.2024 07:42:29 - Start convergenceLoop
+26.02.2024 07:42:29 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.02.2024 07:42:29 - Start calculation ...
+26.02.2024 07:42:29 - Design Modus 1: Clean sheet design!
+26.02.2024 07:42:29 - Settings in Sub-Programs will be checked!
+26.02.2024 07:42:29 - * Checking design point:
+26.02.2024 07:42:29 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.02.2024 07:42:29 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.02.2024 07:42:29 - ----
+26.02.2024 07:42:29 - * Checking fuselage geometry:
+26.02.2024 07:42:29 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.02.2024 07:42:29 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.02.2024 07:42:29 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.02.2024 07:42:29 - ----
+26.02.2024 07:42:29 - * Checking createMissionXML:
+26.02.2024 07:42:29 - - Design mission will be created.
+26.02.2024 07:42:29 - ----
+26.02.2024 07:42:29 - * Checking wing design:
+26.02.2024 07:42:29 - - Wing geometry available in XML file.
+26.02.2024 07:42:29 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.02.2024 07:42:29 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.02.2024 07:42:29 - ----
+26.02.2024 07:42:29 - * Checking empennage design:
+26.02.2024 07:42:29 - - Tail geometry available in XML file.
+26.02.2024 07:42:29 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.02.2024 07:42:29 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.02.2024 07:42:29 - ----
+26.02.2024 07:42:29 - * Checking nacelle design and propulsion integration:
+26.02.2024 07:42:29 - - Nacelles already exist.
+26.02.2024 07:42:29 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.02.2024 07:42:29 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.02.2024 07:42:29 - ----
+26.02.2024 07:42:29 - * Checking systems design:
+26.02.2024 07:42:29 - - systemsDesign is running in design mode.
+26.02.2024 07:42:29 - ----
+26.02.2024 07:42:29 - * Checking mission analysis:
+26.02.2024 07:42:29 - - missionAnalysis is running in design mode.
+26.02.2024 07:42:29 - ----
+26.02.2024 07:42:29 - * Checking performance calculation:
+26.02.2024 07:42:29 - - Take-off and landing performance are estimated.
+26.02.2024 07:42:29 - - Payload-Range diagram is calculated.
+26.02.2024 07:42:29 - ----
+26.02.2024 07:42:29 - Still to be continued? (y/n)
+26.02.2024 07:42:39 - ----------------------------------------
+26.02.2024 07:42:39 - Setup-Tools ...
+26.02.2024 07:42:39 - Start : initialSizing
+26.02.2024 07:42:39 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.02.2024 07:42:39 - ERROR: Error in Setup steps. Error code: 1
+
+26.02.2024 07:42:39 - ---------------------------------------------
+26.02.2024 07:42:39 - Checking Requirements ...
+26.02.2024 07:42:39 - * Checking TLARs ...
+26.02.2024 07:42:39 - * Checking tank volume for design ...
+26.02.2024 07:42:39 - * Checking tank volume for study ...
+26.02.2024 07:42:39 - * Checking reserve fuel ...
+26.02.2024 07:42:39 - * Checking TOM on study mission ...
+26.02.2024 07:42:39 - WARNING: Outputs are written, but may contain errors!
+26.02.2024 07:42:39 - ... calculation finished!
+26.02.2024 07:42:39 - Write output ...
+26.02.2024 07:42:39 - Create Plots ...
+26.02.2024 07:42:39 - Copy Plotting files ...
+26.02.2024 07:42:39 - Write HTML-Report ...
+26.02.2024 07:42:39 - Needed time: 0.166667 min
+26.02.2024 07:42:40 - Finish convergenceLoop
+*******************************************************************************
+26.02.2024 07:46:13 - Start convergenceLoop
+26.02.2024 07:46:13 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.02.2024 07:46:13 - Start calculation ...
+26.02.2024 07:46:14 - Design Modus 1: Clean sheet design!
+26.02.2024 07:46:14 - Settings in Sub-Programs will be checked!
+26.02.2024 07:46:14 - * Checking design point:
+26.02.2024 07:46:14 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.02.2024 07:46:14 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.02.2024 07:46:14 - ----
+26.02.2024 07:46:14 - * Checking fuselage geometry:
+26.02.2024 07:46:14 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.02.2024 07:46:14 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.02.2024 07:46:14 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.02.2024 07:46:14 - ----
+26.02.2024 07:46:14 - * Checking createMissionXML:
+26.02.2024 07:46:14 - - Design mission will be created.
+26.02.2024 07:46:14 - ----
+26.02.2024 07:46:14 - * Checking wing design:
+26.02.2024 07:46:14 - - Wing geometry available in XML file.
+26.02.2024 07:46:14 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.02.2024 07:46:14 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.02.2024 07:46:14 - ----
+26.02.2024 07:46:14 - * Checking empennage design:
+26.02.2024 07:46:14 - - Tail geometry available in XML file.
+26.02.2024 07:46:14 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.02.2024 07:46:14 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.02.2024 07:46:14 - ----
+26.02.2024 07:46:14 - * Checking nacelle design and propulsion integration:
+26.02.2024 07:46:14 - - Nacelles already exist.
+26.02.2024 07:46:14 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.02.2024 07:46:14 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.02.2024 07:46:14 - ----
+26.02.2024 07:46:14 - * Checking systems design:
+26.02.2024 07:46:14 - - systemsDesign is running in design mode.
+26.02.2024 07:46:14 - ----
+26.02.2024 07:46:14 - * Checking mission analysis:
+26.02.2024 07:46:14 - - missionAnalysis is running in design mode.
+26.02.2024 07:46:14 - ----
+26.02.2024 07:46:14 - * Checking performance calculation:
+26.02.2024 07:46:14 - - Take-off and landing performance are estimated.
+26.02.2024 07:46:14 - - Payload-Range diagram is calculated.
+26.02.2024 07:46:14 - ----
+26.02.2024 07:46:14 - Still to be continued? (y/n)
+26.02.2024 07:46:14 - ----------------------------------------
+26.02.2024 07:46:14 - Setup-Tools ...
+26.02.2024 07:46:14 - Start : initialSizing
+26.02.2024 07:46:14 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.02.2024 07:46:14 - ERROR: Error in Setup steps. Error code: 1
+
+26.02.2024 07:46:14 - ---------------------------------------------
+26.02.2024 07:46:14 - Checking Requirements ...
+26.02.2024 07:46:14 - * Checking TLARs ...
+26.02.2024 07:46:14 - * Checking tank volume for design ...
+26.02.2024 07:46:14 - * Checking tank volume for study ...
+26.02.2024 07:46:14 - * Checking reserve fuel ...
+26.02.2024 07:46:14 - * Checking TOM on study mission ...
+26.02.2024 07:46:14 - WARNING: Outputs are written, but may contain errors!
+26.02.2024 07:46:14 - ... calculation finished!
+26.02.2024 07:46:14 - Write output ...
+26.02.2024 07:46:14 - Create Plots ...
+26.02.2024 07:46:14 - Copy Plotting files ...
+26.02.2024 07:46:14 - Write HTML-Report ...
+26.02.2024 07:46:14 - Needed time: 0.0166667 min
+26.02.2024 07:46:14 - Finish convergenceLoop
+*******************************************************************************
+26.02.2024 07:47:17 - Start convergenceLoop
+26.02.2024 07:47:17 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.02.2024 07:47:17 - Start calculation ...
+26.02.2024 07:47:17 - Design Modus 1: Clean sheet design!
+26.02.2024 07:47:17 - Settings in Sub-Programs will be checked!
+26.02.2024 07:47:17 - * Checking design point:
+26.02.2024 07:47:17 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.02.2024 07:47:17 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.02.2024 07:47:17 - ----
+26.02.2024 07:47:17 - * Checking fuselage geometry:
+26.02.2024 07:47:17 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.02.2024 07:47:17 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.02.2024 07:47:17 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.02.2024 07:47:17 - ----
+26.02.2024 07:47:17 - * Checking createMissionXML:
+26.02.2024 07:47:17 - - Design mission will be created.
+26.02.2024 07:47:17 - ----
+26.02.2024 07:47:17 - * Checking wing design:
+26.02.2024 07:47:17 - - Wing geometry available in XML file.
+26.02.2024 07:47:17 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.02.2024 07:47:17 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.02.2024 07:47:17 - ----
+26.02.2024 07:47:17 - * Checking empennage design:
+26.02.2024 07:47:17 - - Tail geometry available in XML file.
+26.02.2024 07:47:17 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.02.2024 07:47:17 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.02.2024 07:47:17 - ----
+26.02.2024 07:47:17 - * Checking nacelle design and propulsion integration:
+26.02.2024 07:47:17 - - Nacelles already exist.
+26.02.2024 07:47:17 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.02.2024 07:47:17 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.02.2024 07:47:17 - ----
+26.02.2024 07:47:17 - * Checking systems design:
+26.02.2024 07:47:17 - - systemsDesign is running in design mode.
+26.02.2024 07:47:17 - ----
+26.02.2024 07:47:17 - * Checking mission analysis:
+26.02.2024 07:47:17 - - missionAnalysis is running in design mode.
+26.02.2024 07:47:17 - ----
+26.02.2024 07:47:17 - * Checking performance calculation:
+26.02.2024 07:47:17 - - Take-off and landing performance are estimated.
+26.02.2024 07:47:17 - - Payload-Range diagram is calculated.
+26.02.2024 07:47:17 - ----
+26.02.2024 07:47:17 - Still to be continued? (y/n)
+26.02.2024 07:47:39 - ----------------------------------------
+26.02.2024 07:47:39 - Setup-Tools ...
+26.02.2024 07:47:39 - Start : initialSizing
+26.02.2024 07:47:40 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.02.2024 07:47:40 - ERROR: Error in Setup steps. Error code: 1
+
+26.02.2024 07:47:40 - ---------------------------------------------
+26.02.2024 07:47:40 - Checking Requirements ...
+26.02.2024 07:47:40 - * Checking TLARs ...
+26.02.2024 07:47:40 - * Checking tank volume for design ...
+26.02.2024 07:47:40 - * Checking tank volume for study ...
+26.02.2024 07:47:40 - * Checking reserve fuel ...
+26.02.2024 07:47:40 - * Checking TOM on study mission ...
+26.02.2024 07:47:40 - WARNING: Outputs are written, but may contain errors!
+26.02.2024 07:47:40 - ... calculation finished!
+26.02.2024 07:47:40 - Write output ...
+26.02.2024 07:47:40 - Create Plots ...
+26.02.2024 07:47:40 - Copy Plotting files ...
+26.02.2024 07:47:40 - Write HTML-Report ...
+26.02.2024 07:47:40 - Needed time: 0.383333 min
+26.02.2024 07:47:40 - Finish convergenceLoop
+*******************************************************************************
+26.02.2024 09:23:23 - Start convergenceLoop
+26.02.2024 09:23:23 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.02.2024 09:23:23 - Start calculation ...
+26.02.2024 09:23:23 - Design Modus 1: Clean sheet design!
+26.02.2024 09:23:23 - Settings in Sub-Programs will be checked!
+26.02.2024 09:23:23 - * Checking design point:
+26.02.2024 09:23:23 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.02.2024 09:23:23 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.02.2024 09:23:23 - ----
+26.02.2024 09:23:23 - * Checking fuselage geometry:
+26.02.2024 09:23:23 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.02.2024 09:23:24 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.02.2024 09:23:24 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.02.2024 09:23:24 - ----
+26.02.2024 09:23:24 - * Checking createMissionXML:
+26.02.2024 09:23:24 - - Design mission will be created.
+26.02.2024 09:23:24 - ----
+26.02.2024 09:23:24 - * Checking wing design:
+26.02.2024 09:23:24 - - Wing geometry available in XML file.
+26.02.2024 09:23:24 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.02.2024 09:23:24 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.02.2024 09:23:24 - ----
+26.02.2024 09:23:24 - * Checking empennage design:
+26.02.2024 09:23:24 - - Tail geometry available in XML file.
+26.02.2024 09:23:24 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.02.2024 09:23:24 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.02.2024 09:23:24 - ----
+26.02.2024 09:23:24 - * Checking nacelle design and propulsion integration:
+26.02.2024 09:23:24 - - Nacelles already exist.
+26.02.2024 09:23:24 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.02.2024 09:23:24 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.02.2024 09:23:24 - ----
+26.02.2024 09:23:24 - * Checking systems design:
+26.02.2024 09:23:24 - - systemsDesign is running in design mode.
+26.02.2024 09:23:24 - ----
+26.02.2024 09:23:24 - * Checking mission analysis:
+26.02.2024 09:23:24 - - missionAnalysis is running in design mode.
+26.02.2024 09:23:24 - ----
+26.02.2024 09:23:24 - * Checking performance calculation:
+26.02.2024 09:23:24 - - Take-off and landing performance are estimated.
+26.02.2024 09:23:24 - - Payload-Range diagram is calculated.
+26.02.2024 09:23:24 - ----
+26.02.2024 09:23:24 - Still to be continued? (y/n)
+26.02.2024 09:23:24 - ----------------------------------------
+26.02.2024 09:23:24 - Setup-Tools ...
+26.02.2024 09:23:24 - Start : initialSizing
+26.02.2024 09:23:24 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.02.2024 09:23:24 - ERROR: Error in Setup steps. Error code: 1
+
+26.02.2024 09:23:24 - ---------------------------------------------
+26.02.2024 09:23:24 - Checking Requirements ...
+26.02.2024 09:23:24 - * Checking TLARs ...
+26.02.2024 09:23:24 - * Checking tank volume for design ...
+26.02.2024 09:23:24 - * Checking tank volume for study ...
+26.02.2024 09:23:24 - * Checking reserve fuel ...
+26.02.2024 09:23:24 - * Checking TOM on study mission ...
+26.02.2024 09:23:24 - WARNING: Outputs are written, but may contain errors!
+26.02.2024 09:23:24 - ... calculation finished!
+26.02.2024 09:23:24 - Write output ...
+26.02.2024 09:23:24 - Create Plots ...
+26.02.2024 09:23:24 - Copy Plotting files ...
+26.02.2024 09:23:24 - Write HTML-Report ...
+26.02.2024 09:23:24 - Needed time: 0.0166667 min
+26.02.2024 09:23:24 - Finish convergenceLoop
+*******************************************************************************
+26.02.2024 09:23:25 - Start convergenceLoop
+26.02.2024 09:23:25 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.02.2024 09:23:25 - Start calculation ...
+26.02.2024 09:23:25 - Design Modus 1: Clean sheet design!
+26.02.2024 09:23:25 - Settings in Sub-Programs will be checked!
+26.02.2024 09:23:25 - * Checking design point:
+26.02.2024 09:23:25 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.02.2024 09:23:25 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.02.2024 09:23:25 - ----
+26.02.2024 09:23:25 - * Checking fuselage geometry:
+26.02.2024 09:23:25 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.02.2024 09:23:25 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.02.2024 09:23:25 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.02.2024 09:23:25 - ----
+26.02.2024 09:23:25 - * Checking createMissionXML:
+26.02.2024 09:23:25 - - Design mission will be created.
+26.02.2024 09:23:25 - ----
+26.02.2024 09:23:25 - * Checking wing design:
+26.02.2024 09:23:25 - - Wing geometry available in XML file.
+26.02.2024 09:23:25 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.02.2024 09:23:25 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.02.2024 09:23:25 - ----
+26.02.2024 09:23:25 - * Checking empennage design:
+26.02.2024 09:23:25 - - Tail geometry available in XML file.
+26.02.2024 09:23:25 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.02.2024 09:23:25 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.02.2024 09:23:25 - ----
+26.02.2024 09:23:25 - * Checking nacelle design and propulsion integration:
+26.02.2024 09:23:25 - - Nacelles already exist.
+26.02.2024 09:23:25 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.02.2024 09:23:25 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.02.2024 09:23:25 - ----
+26.02.2024 09:23:25 - * Checking systems design:
+26.02.2024 09:23:25 - - systemsDesign is running in design mode.
+26.02.2024 09:23:25 - ----
+26.02.2024 09:23:25 - * Checking mission analysis:
+26.02.2024 09:23:25 - - missionAnalysis is running in design mode.
+26.02.2024 09:23:25 - ----
+26.02.2024 09:23:25 - * Checking performance calculation:
+26.02.2024 09:23:25 - - Take-off and landing performance are estimated.
+26.02.2024 09:23:25 - - Payload-Range diagram is calculated.
+26.02.2024 09:23:25 - ----
+26.02.2024 09:23:25 - Still to be continued? (y/n)
+26.02.2024 09:23:25 - ----------------------------------------
+26.02.2024 09:23:25 - Setup-Tools ...
+26.02.2024 09:23:25 - Start : initialSizing
+26.02.2024 09:23:25 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.02.2024 09:23:25 - ERROR: Error in Setup steps. Error code: 1
+
+26.02.2024 09:23:26 - ---------------------------------------------
+26.02.2024 09:23:26 - Checking Requirements ...
+26.02.2024 09:23:26 - * Checking TLARs ...
+26.02.2024 09:23:26 - * Checking tank volume for design ...
+26.02.2024 09:23:26 - * Checking tank volume for study ...
+26.02.2024 09:23:26 - * Checking reserve fuel ...
+26.02.2024 09:23:26 - * Checking TOM on study mission ...
+26.02.2024 09:23:26 - WARNING: Outputs are written, but may contain errors!
+26.02.2024 09:23:26 - ... calculation finished!
+26.02.2024 09:23:26 - Write output ...
+26.02.2024 09:23:26 - Create Plots ...
+26.02.2024 09:23:26 - Copy Plotting files ...
+26.02.2024 09:23:26 - Write HTML-Report ...
+26.02.2024 09:23:26 - Needed time: 0.0166667 min
+26.02.2024 09:23:26 - Finish convergenceLoop
+*******************************************************************************
+26.02.2024 10:57:51 - Start convergenceLoop
+26.02.2024 10:57:51 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.02.2024 10:57:51 - Start calculation ...
+26.02.2024 10:57:51 - Design Modus 1: Clean sheet design!
+26.02.2024 10:57:51 - Settings in Sub-Programs will be checked!
+26.02.2024 10:57:51 - * Checking design point:
+26.02.2024 10:57:51 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.02.2024 10:57:51 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.02.2024 10:57:51 - ----
+26.02.2024 10:57:51 - * Checking fuselage geometry:
+26.02.2024 10:57:51 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.02.2024 10:57:51 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.02.2024 10:57:51 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.02.2024 10:57:51 - ----
+26.02.2024 10:57:51 - * Checking createMissionXML:
+26.02.2024 10:57:51 - - Design mission will be created.
+26.02.2024 10:57:51 - ----
+26.02.2024 10:57:51 - * Checking wing design:
+26.02.2024 10:57:51 - - Wing geometry available in XML file.
+26.02.2024 10:57:51 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.02.2024 10:57:51 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.02.2024 10:57:51 - ----
+26.02.2024 10:57:51 - * Checking empennage design:
+26.02.2024 10:57:51 - - Tail geometry available in XML file.
+26.02.2024 10:57:51 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.02.2024 10:57:51 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.02.2024 10:57:51 - ----
+26.02.2024 10:57:51 - * Checking nacelle design and propulsion integration:
+26.02.2024 10:57:51 - - Nacelles already exist.
+26.02.2024 10:57:51 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.02.2024 10:57:51 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.02.2024 10:57:51 - ----
+26.02.2024 10:57:51 - * Checking systems design:
+26.02.2024 10:57:51 - - systemsDesign is running in design mode.
+26.02.2024 10:57:51 - ----
+26.02.2024 10:57:51 - * Checking mission analysis:
+26.02.2024 10:57:51 - - missionAnalysis is running in design mode.
+26.02.2024 10:57:51 - ----
+26.02.2024 10:57:51 - * Checking performance calculation:
+26.02.2024 10:57:51 - - Take-off and landing performance are estimated.
+26.02.2024 10:57:51 - - Payload-Range diagram is calculated.
+26.02.2024 10:57:51 - ----
+26.02.2024 10:57:51 - Still to be continued? (y/n)
+26.02.2024 10:57:51 - ----------------------------------------
+26.02.2024 10:57:51 - Setup-Tools ...
+26.02.2024 10:57:51 - Start : initialSizing
+26.02.2024 10:57:52 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.02.2024 10:57:52 - ERROR: Error in Setup steps. Error code: 1
+
+26.02.2024 10:57:52 - ---------------------------------------------
+26.02.2024 10:57:52 - Checking Requirements ...
+26.02.2024 10:57:52 - * Checking TLARs ...
+26.02.2024 10:57:52 - * Checking tank volume for design ...
+26.02.2024 10:57:52 - * Checking tank volume for study ...
+26.02.2024 10:57:52 - * Checking reserve fuel ...
+26.02.2024 10:57:52 - * Checking TOM on study mission ...
+26.02.2024 10:57:52 - WARNING: Outputs are written, but may contain errors!
+26.02.2024 10:57:52 - ... calculation finished!
+26.02.2024 10:57:52 - Write output ...
+26.02.2024 10:57:52 - Create Plots ...
+26.02.2024 10:57:52 - Copy Plotting files ...
+26.02.2024 10:57:52 - Write HTML-Report ...
+26.02.2024 10:57:52 - Needed time: 0.0166667 min
+26.02.2024 10:57:52 - Finish convergenceLoop
+*******************************************************************************
+26.02.2024 12:26:38 - Start convergenceLoop
+26.02.2024 12:26:38 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.02.2024 12:26:38 - Start calculation ...
+26.02.2024 12:26:38 - Design Modus 1: Clean sheet design!
+26.02.2024 12:26:38 - Settings in Sub-Programs will be checked!
+26.02.2024 12:26:38 - * Checking design point:
+26.02.2024 12:26:38 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.02.2024 12:26:38 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.02.2024 12:26:38 - ----
+26.02.2024 12:26:38 - * Checking fuselage geometry:
+26.02.2024 12:26:38 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.02.2024 12:26:38 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.02.2024 12:26:38 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.02.2024 12:26:38 - ----
+26.02.2024 12:26:38 - * Checking createMissionXML:
+26.02.2024 12:26:38 - - Design mission will be created.
+26.02.2024 12:26:38 - ----
+26.02.2024 12:26:38 - * Checking wing design:
+26.02.2024 12:26:38 - - Wing geometry available in XML file.
+26.02.2024 12:26:38 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.02.2024 12:26:38 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.02.2024 12:26:38 - ----
+26.02.2024 12:26:38 - * Checking empennage design:
+26.02.2024 12:26:38 - - Tail geometry available in XML file.
+26.02.2024 12:26:38 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.02.2024 12:26:38 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.02.2024 12:26:38 - ----
+26.02.2024 12:26:38 - * Checking nacelle design and propulsion integration:
+26.02.2024 12:26:38 - - Nacelles already exist.
+26.02.2024 12:26:38 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.02.2024 12:26:38 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.02.2024 12:26:38 - ----
+26.02.2024 12:26:38 - * Checking systems design:
+26.02.2024 12:26:38 - - systemsDesign is running in design mode.
+26.02.2024 12:26:38 - ----
+26.02.2024 12:26:38 - * Checking mission analysis:
+26.02.2024 12:26:38 - - missionAnalysis is running in design mode.
+26.02.2024 12:26:38 - ----
+26.02.2024 12:26:38 - * Checking performance calculation:
+26.02.2024 12:26:38 - - Take-off and landing performance are estimated.
+26.02.2024 12:26:38 - - Payload-Range diagram is calculated.
+26.02.2024 12:26:38 - ----
+26.02.2024 12:26:38 - Still to be continued? (y/n)
+26.02.2024 12:26:38 - ----------------------------------------
+26.02.2024 12:26:38 - Setup-Tools ...
+26.02.2024 12:26:38 - Start : initialSizing
+26.02.2024 12:26:38 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.02.2024 12:26:38 - ERROR: Error in Setup steps. Error code: 1
+
+26.02.2024 12:26:38 - ---------------------------------------------
+26.02.2024 12:26:38 - Checking Requirements ...
+26.02.2024 12:26:38 - * Checking TLARs ...
+26.02.2024 12:26:38 - * Checking tank volume for design ...
+26.02.2024 12:26:38 - * Checking tank volume for study ...
+26.02.2024 12:26:38 - * Checking reserve fuel ...
+26.02.2024 12:26:38 - * Checking TOM on study mission ...
+26.02.2024 12:26:38 - WARNING: Outputs are written, but may contain errors!
+26.02.2024 12:26:38 - ... calculation finished!
+26.02.2024 12:26:38 - Write output ...
+26.02.2024 12:26:38 - Create Plots ...
+26.02.2024 12:26:38 - Copy Plotting files ...
+26.02.2024 12:26:38 - Write HTML-Report ...
+26.02.2024 12:26:38 - Needed time: 0 min
+26.02.2024 12:26:39 - Finish convergenceLoop
+*******************************************************************************
+26.02.2024 13:52:18 - Start convergenceLoop
+26.02.2024 13:52:18 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.02.2024 13:52:18 - Start calculation ...
+26.02.2024 13:52:18 - Design Modus 1: Clean sheet design!
+26.02.2024 13:52:18 - Settings in Sub-Programs will be checked!
+26.02.2024 13:52:18 - * Checking design point:
+26.02.2024 13:52:18 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.02.2024 13:52:18 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.02.2024 13:52:18 - ----
+26.02.2024 13:52:18 - * Checking fuselage geometry:
+26.02.2024 13:52:18 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.02.2024 13:52:18 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.02.2024 13:52:18 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.02.2024 13:52:18 - ----
+26.02.2024 13:52:18 - * Checking createMissionXML:
+26.02.2024 13:52:18 - - Design mission will be created.
+26.02.2024 13:52:18 - ----
+26.02.2024 13:52:18 - * Checking wing design:
+26.02.2024 13:52:18 - - Wing geometry available in XML file.
+26.02.2024 13:52:18 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.02.2024 13:52:18 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.02.2024 13:52:18 - ----
+26.02.2024 13:52:18 - * Checking empennage design:
+26.02.2024 13:52:18 - - Tail geometry available in XML file.
+26.02.2024 13:52:18 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.02.2024 13:52:18 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.02.2024 13:52:18 - ----
+26.02.2024 13:52:18 - * Checking nacelle design and propulsion integration:
+26.02.2024 13:52:18 - - Nacelles already exist.
+26.02.2024 13:52:18 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.02.2024 13:52:18 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.02.2024 13:52:18 - ----
+26.02.2024 13:52:18 - * Checking systems design:
+26.02.2024 13:52:18 - - systemsDesign is running in design mode.
+26.02.2024 13:52:18 - ----
+26.02.2024 13:52:18 - * Checking mission analysis:
+26.02.2024 13:52:18 - - missionAnalysis is running in design mode.
+26.02.2024 13:52:18 - ----
+26.02.2024 13:52:18 - * Checking performance calculation:
+26.02.2024 13:52:18 - - Take-off and landing performance are estimated.
+26.02.2024 13:52:18 - - Payload-Range diagram is calculated.
+26.02.2024 13:52:18 - ----
+26.02.2024 13:52:18 - Still to be continued? (y/n)
+26.02.2024 13:52:18 - ----------------------------------------
+26.02.2024 13:52:18 - Setup-Tools ...
+26.02.2024 13:52:18 - Start : initialSizing
+26.02.2024 13:52:18 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.02.2024 13:52:18 - ERROR: Error in Setup steps. Error code: 1
+
+26.02.2024 13:52:18 - ---------------------------------------------
+26.02.2024 13:52:18 - Checking Requirements ...
+26.02.2024 13:52:18 - * Checking TLARs ...
+26.02.2024 13:52:18 - * Checking tank volume for design ...
+26.02.2024 13:52:18 - * Checking tank volume for study ...
+26.02.2024 13:52:18 - * Checking reserve fuel ...
+26.02.2024 13:52:18 - * Checking TOM on study mission ...
+26.02.2024 13:52:18 - WARNING: Outputs are written, but may contain errors!
+26.02.2024 13:52:18 - ... calculation finished!
+26.02.2024 13:52:18 - Write output ...
+26.02.2024 13:52:18 - Create Plots ...
+26.02.2024 13:52:18 - Copy Plotting files ...
+26.02.2024 13:52:18 - Write HTML-Report ...
+26.02.2024 13:52:18 - Needed time: 0 min
+26.02.2024 13:52:19 - Finish convergenceLoop
+*******************************************************************************
+26.02.2024 15:15:08 - Start convergenceLoop
+26.02.2024 15:15:08 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.02.2024 15:15:08 - Start calculation ...
+26.02.2024 15:15:08 - Design Modus 1: Clean sheet design!
+26.02.2024 15:15:08 - Settings in Sub-Programs will be checked!
+26.02.2024 15:15:08 - * Checking design point:
+26.02.2024 15:15:08 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.02.2024 15:15:08 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.02.2024 15:15:08 - ----
+26.02.2024 15:15:08 - * Checking fuselage geometry:
+26.02.2024 15:15:08 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.02.2024 15:15:08 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.02.2024 15:15:08 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.02.2024 15:15:08 - ----
+26.02.2024 15:15:08 - * Checking createMissionXML:
+26.02.2024 15:15:08 - - Design mission will be created.
+26.02.2024 15:15:08 - ----
+26.02.2024 15:15:08 - * Checking wing design:
+26.02.2024 15:15:08 - - Wing geometry available in XML file.
+26.02.2024 15:15:08 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.02.2024 15:15:08 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.02.2024 15:15:08 - ----
+26.02.2024 15:15:08 - * Checking empennage design:
+26.02.2024 15:15:08 - - Tail geometry available in XML file.
+26.02.2024 15:15:08 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.02.2024 15:15:08 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.02.2024 15:15:08 - ----
+26.02.2024 15:15:08 - * Checking nacelle design and propulsion integration:
+26.02.2024 15:15:08 - - Nacelles already exist.
+26.02.2024 15:15:08 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.02.2024 15:15:08 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.02.2024 15:15:08 - ----
+26.02.2024 15:15:08 - * Checking systems design:
+26.02.2024 15:15:08 - - systemsDesign is running in design mode.
+26.02.2024 15:15:08 - ----
+26.02.2024 15:15:08 - * Checking mission analysis:
+26.02.2024 15:15:08 - - missionAnalysis is running in design mode.
+26.02.2024 15:15:08 - ----
+26.02.2024 15:15:08 - * Checking performance calculation:
+26.02.2024 15:15:08 - - Take-off and landing performance are estimated.
+26.02.2024 15:15:08 - - Payload-Range diagram is calculated.
+26.02.2024 15:15:08 - ----
+26.02.2024 15:15:08 - Still to be continued? (y/n)
+26.02.2024 15:15:08 - ----------------------------------------
+26.02.2024 15:15:08 - Setup-Tools ...
+26.02.2024 15:15:08 - Start : initialSizing
+*******************************************************************************
+27.02.2024 09:00:15 - Start convergenceLoop
+27.02.2024 09:00:15 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+27.02.2024 09:00:15 - Start calculation ...
+27.02.2024 09:00:15 - Design Modus 1: Clean sheet design!
+27.02.2024 09:00:15 - Settings in Sub-Programs will be checked!
+27.02.2024 09:00:15 - * Checking design point:
+27.02.2024 09:00:15 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+27.02.2024 09:00:15 - The in the Setup-Steps selected initialSizing module overwrites them.
+27.02.2024 09:00:15 - ----
+27.02.2024 09:00:15 - * Checking fuselage geometry:
+27.02.2024 09:00:15 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+27.02.2024 09:00:15 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+27.02.2024 09:00:15 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+27.02.2024 09:00:15 - ----
+27.02.2024 09:00:15 - * Checking createMissionXML:
+27.02.2024 09:00:15 - - Design mission will be created.
+27.02.2024 09:00:15 - ----
+27.02.2024 09:00:15 - * Checking wing design:
+27.02.2024 09:00:15 - - Wing geometry available in XML file.
+27.02.2024 09:00:15 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+27.02.2024 09:00:15 - - Existing wing geometry will be overwritten by initialWingSizing module.
+27.02.2024 09:00:15 - ----
+27.02.2024 09:00:15 - * Checking empennage design:
+27.02.2024 09:00:15 - - Tail geometry available in XML file.
+27.02.2024 09:00:15 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+27.02.2024 09:00:15 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+27.02.2024 09:00:15 - ----
+27.02.2024 09:00:15 - * Checking nacelle design and propulsion integration:
+27.02.2024 09:00:15 - - Nacelles already exist.
+27.02.2024 09:00:15 - - Nacelle geometries will be designed by the propulsion integration module.!
+27.02.2024 09:00:15 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+27.02.2024 09:00:15 - ----
+27.02.2024 09:00:15 - * Checking systems design:
+27.02.2024 09:00:15 - - systemsDesign is running in design mode.
+27.02.2024 09:00:15 - ----
+27.02.2024 09:00:15 - * Checking mission analysis:
+27.02.2024 09:00:15 - - missionAnalysis is running in design mode.
+27.02.2024 09:00:15 - ----
+27.02.2024 09:00:15 - * Checking performance calculation:
+27.02.2024 09:00:15 - - Take-off and landing performance are estimated.
+27.02.2024 09:00:15 - - Payload-Range diagram is calculated.
+27.02.2024 09:00:15 - ----
+27.02.2024 09:00:15 - Still to be continued? (y/n)
+27.02.2024 09:00:15 - ----------------------------------------
+27.02.2024 09:00:15 - Setup-Tools ...
+27.02.2024 09:00:15 - Start : initialSizing
+27.02.2024 09:00:16 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+27.02.2024 09:00:16 - ERROR: Error in Setup steps. Error code: 1
+
+27.02.2024 09:00:16 - ---------------------------------------------
+27.02.2024 09:00:16 - Checking Requirements ...
+27.02.2024 09:00:16 - * Checking TLARs ...
+27.02.2024 09:00:16 - * Checking tank volume for design ...
+27.02.2024 09:00:16 - * Checking tank volume for study ...
+27.02.2024 09:00:16 - * Checking reserve fuel ...
+27.02.2024 09:00:16 - * Checking TOM on study mission ...
+27.02.2024 09:00:16 - WARNING: Outputs are written, but may contain errors!
+27.02.2024 09:00:16 - ... calculation finished!
+27.02.2024 09:00:16 - Write output ...
+27.02.2024 09:00:16 - Create Plots ...
+27.02.2024 09:00:16 - Copy Plotting files ...
+27.02.2024 09:00:16 - Write HTML-Report ...
+27.02.2024 09:00:16 - Needed time: 0.0166667 min
+27.02.2024 09:00:16 - Finish convergenceLoop
+*******************************************************************************
+27.02.2024 09:01:09 - Start convergenceLoop
+27.02.2024 09:01:09 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+27.02.2024 09:01:09 - Start calculation ...
+27.02.2024 09:01:10 - Design Modus 1: Clean sheet design!
+27.02.2024 09:01:10 - Settings in Sub-Programs will be checked!
+27.02.2024 09:01:10 - * Checking design point:
+27.02.2024 09:01:10 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+27.02.2024 09:01:10 - The in the Setup-Steps selected initialSizing module overwrites them.
+27.02.2024 09:01:10 - ----
+27.02.2024 09:01:10 - * Checking fuselage geometry:
+27.02.2024 09:01:10 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+27.02.2024 09:01:10 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+27.02.2024 09:01:10 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+27.02.2024 09:01:10 - ----
+27.02.2024 09:01:10 - * Checking createMissionXML:
+27.02.2024 09:01:10 - - Design mission will be created.
+27.02.2024 09:01:10 - ----
+27.02.2024 09:01:10 - * Checking wing design:
+27.02.2024 09:01:10 - - Wing geometry available in XML file.
+27.02.2024 09:01:10 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+27.02.2024 09:01:10 - - Existing wing geometry will be overwritten by initialWingSizing module.
+27.02.2024 09:01:10 - ----
+27.02.2024 09:01:10 - * Checking empennage design:
+27.02.2024 09:01:10 - - Tail geometry available in XML file.
+27.02.2024 09:01:10 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+27.02.2024 09:01:10 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+27.02.2024 09:01:10 - ----
+27.02.2024 09:01:10 - * Checking nacelle design and propulsion integration:
+27.02.2024 09:01:10 - - Nacelles already exist.
+27.02.2024 09:01:10 - - Nacelle geometries will be designed by the propulsion integration module.!
+27.02.2024 09:01:10 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+27.02.2024 09:01:10 - ----
+27.02.2024 09:01:10 - * Checking systems design:
+27.02.2024 09:01:10 - - systemsDesign is running in design mode.
+27.02.2024 09:01:10 - ----
+27.02.2024 09:01:10 - * Checking mission analysis:
+27.02.2024 09:01:10 - - missionAnalysis is running in design mode.
+27.02.2024 09:01:10 - ----
+27.02.2024 09:01:10 - * Checking performance calculation:
+27.02.2024 09:01:10 - - Take-off and landing performance are estimated.
+27.02.2024 09:01:10 - - Payload-Range diagram is calculated.
+27.02.2024 09:01:10 - ----
+27.02.2024 09:01:10 - Still to be continued? (y/n)
+27.02.2024 09:01:10 - ----------------------------------------
+27.02.2024 09:01:10 - Setup-Tools ...
+27.02.2024 09:01:10 - Start : initialSizing
+27.02.2024 09:01:10 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+27.02.2024 09:01:10 - ERROR: Error in Setup steps. Error code: 1
+
+27.02.2024 09:01:10 - ---------------------------------------------
+27.02.2024 09:01:10 - Checking Requirements ...
+27.02.2024 09:01:10 - * Checking TLARs ...
+27.02.2024 09:01:10 - * Checking tank volume for design ...
+27.02.2024 09:01:10 - * Checking tank volume for study ...
+27.02.2024 09:01:10 - * Checking reserve fuel ...
+27.02.2024 09:01:10 - * Checking TOM on study mission ...
+27.02.2024 09:01:10 - WARNING: Outputs are written, but may contain errors!
+27.02.2024 09:01:10 - ... calculation finished!
+27.02.2024 09:01:10 - Write output ...
+27.02.2024 09:01:10 - Create Plots ...
+27.02.2024 09:01:10 - Copy Plotting files ...
+27.02.2024 09:01:10 - Write HTML-Report ...
+27.02.2024 09:01:10 - Needed time: 0.0166667 min
+27.02.2024 09:01:10 - Finish convergenceLoop
+*******************************************************************************
+27.02.2024 10:17:40 - Start convergenceLoop
+27.02.2024 10:17:40 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+27.02.2024 10:17:40 - Start calculation ...
+27.02.2024 10:17:40 - Design Modus 1: Clean sheet design!
+27.02.2024 10:17:40 - Settings in Sub-Programs will be checked!
+27.02.2024 10:17:40 - * Checking design point:
+27.02.2024 10:17:40 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+27.02.2024 10:17:40 - The in the Setup-Steps selected initialSizing module overwrites them.
+27.02.2024 10:17:40 - ----
+27.02.2024 10:17:40 - * Checking fuselage geometry:
+27.02.2024 10:17:40 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+27.02.2024 10:17:40 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+27.02.2024 10:17:40 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+27.02.2024 10:17:40 - ----
+27.02.2024 10:17:40 - * Checking createMissionXML:
+27.02.2024 10:17:40 - - Design mission will be created.
+27.02.2024 10:17:40 - ----
+27.02.2024 10:17:40 - * Checking wing design:
+27.02.2024 10:17:40 - - Wing geometry available in XML file.
+27.02.2024 10:17:40 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+27.02.2024 10:17:40 - - Existing wing geometry will be overwritten by initialWingSizing module.
+27.02.2024 10:17:40 - ----
+27.02.2024 10:17:40 - * Checking empennage design:
+27.02.2024 10:17:40 - - Tail geometry available in XML file.
+27.02.2024 10:17:40 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+27.02.2024 10:17:40 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+27.02.2024 10:17:40 - ----
+27.02.2024 10:17:40 - * Checking nacelle design and propulsion integration:
+27.02.2024 10:17:40 - - Nacelles already exist.
+27.02.2024 10:17:40 - - Nacelle geometries will be designed by the propulsion integration module.!
+27.02.2024 10:17:40 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+27.02.2024 10:17:40 - ----
+27.02.2024 10:17:40 - * Checking systems design:
+27.02.2024 10:17:40 - - systemsDesign is running in design mode.
+27.02.2024 10:17:40 - ----
+27.02.2024 10:17:40 - * Checking mission analysis:
+27.02.2024 10:17:40 - - missionAnalysis is running in design mode.
+27.02.2024 10:17:40 - ----
+27.02.2024 10:17:40 - * Checking performance calculation:
+27.02.2024 10:17:40 - - Take-off and landing performance are estimated.
+27.02.2024 10:17:40 - - Payload-Range diagram is calculated.
+27.02.2024 10:17:40 - ----
+27.02.2024 10:17:40 - Still to be continued? (y/n)
+27.02.2024 10:17:41 - ----------------------------------------
+27.02.2024 10:17:41 - Setup-Tools ...
+27.02.2024 10:17:41 - Start : initialSizing
+27.02.2024 10:17:41 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+27.02.2024 10:17:41 - ERROR: Error in Setup steps. Error code: 1
+
+27.02.2024 10:17:41 - ---------------------------------------------
+27.02.2024 10:17:41 - Checking Requirements ...
+27.02.2024 10:17:41 - * Checking TLARs ...
+27.02.2024 10:17:41 - * Checking tank volume for design ...
+27.02.2024 10:17:41 - * Checking tank volume for study ...
+27.02.2024 10:17:41 - * Checking reserve fuel ...
+27.02.2024 10:17:41 - * Checking TOM on study mission ...
+27.02.2024 10:17:41 - WARNING: Outputs are written, but may contain errors!
+27.02.2024 10:17:41 - ... calculation finished!
+27.02.2024 10:17:41 - Write output ...
+27.02.2024 10:17:41 - Create Plots ...
+27.02.2024 10:17:41 - Copy Plotting files ...
+27.02.2024 10:17:41 - Write HTML-Report ...
+27.02.2024 10:17:41 - Needed time: 0.0166667 min
+27.02.2024 10:17:41 - Finish convergenceLoop
+*******************************************************************************
+28.02.2024 10:44:59 - Start convergenceLoop
+28.02.2024 10:44:59 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+28.02.2024 10:44:59 - Start calculation ...
+28.02.2024 10:44:59 - Design Modus 1: Clean sheet design!
+28.02.2024 10:44:59 - Settings in Sub-Programs will be checked!
+28.02.2024 10:44:59 - * Checking design point:
+28.02.2024 10:44:59 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+28.02.2024 10:44:59 - The in the Setup-Steps selected initialSizing module overwrites them.
+28.02.2024 10:44:59 - ----
+28.02.2024 10:44:59 - * Checking fuselage geometry:
+28.02.2024 10:44:59 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+28.02.2024 10:44:59 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+28.02.2024 10:44:59 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+28.02.2024 10:44:59 - ----
+28.02.2024 10:44:59 - * Checking createMissionXML:
+28.02.2024 10:44:59 - - Design mission will be created.
+28.02.2024 10:44:59 - ----
+28.02.2024 10:44:59 - * Checking wing design:
+28.02.2024 10:44:59 - - Wing geometry available in XML file.
+28.02.2024 10:44:59 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+28.02.2024 10:44:59 - - Existing wing geometry will be overwritten by initialWingSizing module.
+28.02.2024 10:44:59 - ----
+28.02.2024 10:44:59 - * Checking empennage design:
+28.02.2024 10:44:59 - - Tail geometry available in XML file.
+28.02.2024 10:44:59 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+28.02.2024 10:44:59 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+28.02.2024 10:44:59 - ----
+28.02.2024 10:44:59 - * Checking nacelle design and propulsion integration:
+28.02.2024 10:44:59 - - Nacelles already exist.
+28.02.2024 10:44:59 - - Nacelle geometries will be designed by the propulsion integration module.!
+28.02.2024 10:44:59 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+28.02.2024 10:44:59 - ----
+28.02.2024 10:44:59 - * Checking systems design:
+28.02.2024 10:44:59 - - systemsDesign is running in design mode.
+28.02.2024 10:44:59 - ----
+28.02.2024 10:44:59 - * Checking mission analysis:
+28.02.2024 10:44:59 - - missionAnalysis is running in design mode.
+28.02.2024 10:44:59 - ----
+28.02.2024 10:44:59 - * Checking performance calculation:
+28.02.2024 10:44:59 - - Take-off and landing performance are estimated.
+28.02.2024 10:44:59 - - Payload-Range diagram is calculated.
+28.02.2024 10:44:59 - ----
+28.02.2024 10:44:59 - Still to be continued? (y/n)
+28.02.2024 10:44:59 - ----------------------------------------
+28.02.2024 10:44:59 - Setup-Tools ...
+28.02.2024 10:44:59 - Start : initialSizing
+28.02.2024 10:44:59 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+28.02.2024 10:44:59 - ERROR: Error in Setup steps. Error code: 1
+
+28.02.2024 10:44:59 - ---------------------------------------------
+28.02.2024 10:44:59 - Checking Requirements ...
+28.02.2024 10:45:00 - * Checking TLARs ...
+28.02.2024 10:45:00 - * Checking tank volume for design ...
+28.02.2024 10:45:00 - * Checking tank volume for study ...
+28.02.2024 10:45:00 - * Checking reserve fuel ...
+28.02.2024 10:45:00 - * Checking TOM on study mission ...
+28.02.2024 10:45:00 - WARNING: Outputs are written, but may contain errors!
+28.02.2024 10:45:00 - ... calculation finished!
+28.02.2024 10:45:00 - Write output ...
+28.02.2024 10:45:00 - Create Plots ...
+28.02.2024 10:45:00 - Copy Plotting files ...
+28.02.2024 10:45:00 - Write HTML-Report ...
+28.02.2024 10:45:00 - Needed time: 0.0166667 min
+28.02.2024 10:45:00 - Finish convergenceLoop
+*******************************************************************************
+06.03.2024 15:56:23 - Start convergenceLoop
+06.03.2024 15:56:23 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+06.03.2024 15:56:23 - Start calculation ...
+06.03.2024 15:56:23 - Design Modus 1: Clean sheet design!
+06.03.2024 15:56:23 - Settings in Sub-Programs will be checked!
+06.03.2024 15:56:23 - * Checking design point:
+06.03.2024 15:56:23 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+06.03.2024 15:56:23 - The in the Setup-Steps selected initialSizing module overwrites them.
+06.03.2024 15:56:23 - ----
+06.03.2024 15:56:23 - * Checking fuselage geometry:
+06.03.2024 15:56:23 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+06.03.2024 15:56:23 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+06.03.2024 15:56:23 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+06.03.2024 15:56:23 - ----
+06.03.2024 15:56:23 - * Checking createMissionXML:
+06.03.2024 15:56:23 - - Design mission will be created.
+06.03.2024 15:56:23 - ----
+06.03.2024 15:56:23 - * Checking wing design:
+06.03.2024 15:56:23 - - Wing geometry available in XML file.
+06.03.2024 15:56:23 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+06.03.2024 15:56:23 - - Existing wing geometry will be overwritten by initialWingSizing module.
+06.03.2024 15:56:23 - ----
+06.03.2024 15:56:23 - * Checking empennage design:
+06.03.2024 15:56:23 - - Tail geometry available in XML file.
+06.03.2024 15:56:23 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+06.03.2024 15:56:23 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+06.03.2024 15:56:23 - ----
+06.03.2024 15:56:23 - * Checking nacelle design and propulsion integration:
+06.03.2024 15:56:23 - - Nacelles already exist.
+06.03.2024 15:56:23 - - Nacelle geometries will be designed by the propulsion integration module.!
+06.03.2024 15:56:23 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+06.03.2024 15:56:23 - ----
+06.03.2024 15:56:23 - * Checking systems design:
+06.03.2024 15:56:23 - - systemsDesign is running in design mode.
+06.03.2024 15:56:23 - ----
+06.03.2024 15:56:23 - * Checking mission analysis:
+06.03.2024 15:56:23 - - missionAnalysis is running in design mode.
+06.03.2024 15:56:23 - ----
+06.03.2024 15:56:23 - * Checking performance calculation:
+06.03.2024 15:56:23 - - Take-off and landing performance are estimated.
+06.03.2024 15:56:23 - - Payload-Range diagram is calculated.
+06.03.2024 15:56:23 - ----
+06.03.2024 15:56:23 - Still to be continued? (y/n)
+06.03.2024 15:56:23 - ----------------------------------------
+06.03.2024 15:56:23 - Setup-Tools ...
+06.03.2024 15:56:23 - Start : initialSizing
+06.03.2024 15:56:24 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+06.03.2024 15:56:24 - ERROR: Error in Setup steps. Error code: 1
+
+06.03.2024 15:56:24 - ---------------------------------------------
+06.03.2024 15:56:24 - Checking Requirements ...
+06.03.2024 15:56:24 - * Checking TLARs ...
+06.03.2024 15:56:24 - * Checking tank volume for design ...
+06.03.2024 15:56:24 - * Checking tank volume for study ...
+06.03.2024 15:56:24 - * Checking reserve fuel ...
+06.03.2024 15:56:24 - * Checking TOM on study mission ...
+06.03.2024 15:56:24 - WARNING: Outputs are written, but may contain errors!
+06.03.2024 15:56:24 - ... calculation finished!
+06.03.2024 15:56:24 - Write output ...
+06.03.2024 15:56:24 - Create Plots ...
+06.03.2024 15:56:24 - Copy Plotting files ...
+06.03.2024 15:56:24 - Write HTML-Report ...
+06.03.2024 15:56:24 - Needed time: 0.0166667 min
+06.03.2024 15:56:24 - Finish convergenceLoop
+*******************************************************************************
+13.03.2024 09:21:23 - Start convergenceLoop
+13.03.2024 09:21:23 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+13.03.2024 09:21:23 - Start calculation ...
+13.03.2024 09:21:23 - Design Modus 1: Clean sheet design!
+13.03.2024 09:21:23 - Settings in Sub-Programs will be checked!
+13.03.2024 09:21:23 - * Checking design point:
+13.03.2024 09:21:23 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+13.03.2024 09:21:23 - The in the Setup-Steps selected initialSizing module overwrites them.
+13.03.2024 09:21:23 - ----
+13.03.2024 09:21:23 - * Checking fuselage geometry:
+13.03.2024 09:21:23 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+13.03.2024 09:21:23 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+13.03.2024 09:21:23 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+13.03.2024 09:21:23 - ----
+13.03.2024 09:21:23 - * Checking createMissionXML:
+13.03.2024 09:21:23 - - Design mission will be created.
+13.03.2024 09:21:23 - ----
+13.03.2024 09:21:23 - * Checking wing design:
+13.03.2024 09:21:23 - - Wing geometry available in XML file.
+13.03.2024 09:21:23 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+13.03.2024 09:21:23 - - Existing wing geometry will be overwritten by initialWingSizing module.
+13.03.2024 09:21:23 - ----
+13.03.2024 09:21:23 - * Checking empennage design:
+13.03.2024 09:21:23 - - Tail geometry available in XML file.
+13.03.2024 09:21:23 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+13.03.2024 09:21:23 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+13.03.2024 09:21:23 - ----
+13.03.2024 09:21:23 - * Checking nacelle design and propulsion integration:
+13.03.2024 09:21:23 - - Nacelles already exist.
+13.03.2024 09:21:23 - - Nacelle geometries will be designed by the propulsion integration module.!
+13.03.2024 09:21:23 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+13.03.2024 09:21:23 - ----
+13.03.2024 09:21:23 - * Checking systems design:
+13.03.2024 09:21:23 - - systemsDesign is running in design mode.
+13.03.2024 09:21:23 - ----
+13.03.2024 09:21:23 - * Checking mission analysis:
+13.03.2024 09:21:23 - - missionAnalysis is running in design mode.
+13.03.2024 09:21:23 - ----
+13.03.2024 09:21:23 - * Checking performance calculation:
+13.03.2024 09:21:23 - - Take-off and landing performance are estimated.
+13.03.2024 09:21:23 - - Payload-Range diagram is calculated.
+13.03.2024 09:21:23 - ----
+13.03.2024 09:21:23 - Still to be continued? (y/n)
+13.03.2024 09:21:23 - ----------------------------------------
+13.03.2024 09:21:23 - Setup-Tools ...
+13.03.2024 09:21:23 - Start : initialSizing
+13.03.2024 09:21:24 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+13.03.2024 09:21:24 - ERROR: Error in Setup steps. Error code: 1
+
+13.03.2024 09:21:24 - ---------------------------------------------
+13.03.2024 09:21:24 - Checking Requirements ...
+13.03.2024 09:21:24 - * Checking TLARs ...
+13.03.2024 09:21:24 - * Checking tank volume for design ...
+13.03.2024 09:21:24 - * Checking tank volume for study ...
+13.03.2024 09:21:24 - * Checking reserve fuel ...
+13.03.2024 09:21:24 - * Checking TOM on study mission ...
+13.03.2024 09:21:24 - WARNING: Outputs are written, but may contain errors!
+13.03.2024 09:21:24 - ... calculation finished!
+13.03.2024 09:21:24 - Write output ...
+13.03.2024 09:21:24 - Create Plots ...
+13.03.2024 09:21:24 - Copy Plotting files ...
+13.03.2024 09:21:24 - Write HTML-Report ...
+13.03.2024 09:21:24 - Needed time: 0.0166667 min
+13.03.2024 09:21:24 - Finish convergenceLoop
+*******************************************************************************
+13.03.2024 12:41:43 - Start convergenceLoop
+13.03.2024 12:41:43 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+13.03.2024 12:41:43 - Start calculation ...
+13.03.2024 12:41:43 - Design Modus 1: Clean sheet design!
+13.03.2024 12:41:43 - Settings in Sub-Programs will be checked!
+13.03.2024 12:41:43 - * Checking design point:
+13.03.2024 12:41:43 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+13.03.2024 12:41:43 - The in the Setup-Steps selected initialSizing module overwrites them.
+13.03.2024 12:41:43 - ----
+13.03.2024 12:41:43 - * Checking fuselage geometry:
+13.03.2024 12:41:43 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+13.03.2024 12:41:43 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+13.03.2024 12:41:43 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+13.03.2024 12:41:43 - ----
+13.03.2024 12:41:43 - * Checking createMissionXML:
+13.03.2024 12:41:43 - - Design mission will be created.
+13.03.2024 12:41:43 - ----
+13.03.2024 12:41:43 - * Checking wing design:
+13.03.2024 12:41:43 - - Wing geometry available in XML file.
+13.03.2024 12:41:43 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+13.03.2024 12:41:43 - - Existing wing geometry will be overwritten by initialWingSizing module.
+13.03.2024 12:41:43 - ----
+13.03.2024 12:41:43 - * Checking empennage design:
+13.03.2024 12:41:43 - - Tail geometry available in XML file.
+13.03.2024 12:41:43 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+13.03.2024 12:41:43 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+13.03.2024 12:41:43 - ----
+13.03.2024 12:41:43 - * Checking nacelle design and propulsion integration:
+13.03.2024 12:41:43 - - Nacelles already exist.
+13.03.2024 12:41:43 - - Nacelle geometries will be designed by the propulsion integration module.!
+13.03.2024 12:41:43 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+13.03.2024 12:41:43 - ----
+13.03.2024 12:41:43 - * Checking systems design:
+13.03.2024 12:41:43 - - systemsDesign is running in design mode.
+13.03.2024 12:41:43 - ----
+13.03.2024 12:41:43 - * Checking mission analysis:
+13.03.2024 12:41:43 - - missionAnalysis is running in design mode.
+13.03.2024 12:41:43 - ----
+13.03.2024 12:41:43 - * Checking performance calculation:
+13.03.2024 12:41:43 - - Take-off and landing performance are estimated.
+13.03.2024 12:41:43 - - Payload-Range diagram is calculated.
+13.03.2024 12:41:43 - ----
+13.03.2024 12:41:43 - Still to be continued? (y/n)
+13.03.2024 12:41:43 - ----------------------------------------
+13.03.2024 12:41:43 - Setup-Tools ...
+13.03.2024 12:41:43 - Start : initialSizing
+13.03.2024 12:41:44 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+13.03.2024 12:41:44 - ERROR: Error in Setup steps. Error code: 1
+
+13.03.2024 12:41:44 - ---------------------------------------------
+13.03.2024 12:41:44 - Checking Requirements ...
+13.03.2024 12:41:44 - * Checking TLARs ...
+13.03.2024 12:41:44 - * Checking tank volume for design ...
+13.03.2024 12:41:44 - * Checking tank volume for study ...
+13.03.2024 12:41:44 - * Checking reserve fuel ...
+13.03.2024 12:41:44 - * Checking TOM on study mission ...
+13.03.2024 12:41:44 - WARNING: Outputs are written, but may contain errors!
+13.03.2024 12:41:44 - ... calculation finished!
+13.03.2024 12:41:44 - Write output ...
+13.03.2024 12:41:44 - Create Plots ...
+13.03.2024 12:41:44 - Copy Plotting files ...
+13.03.2024 12:41:44 - Write HTML-Report ...
+13.03.2024 12:41:44 - Needed time: 0.0166667 min
+13.03.2024 12:41:44 - Finish convergenceLoop
+*******************************************************************************
+05.06.2024 16:28:53 - Start convergenceLoop
+05.06.2024 16:28:53 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+05.06.2024 16:28:53 - Start calculation ...
+05.06.2024 16:28:53 - Design Modus 1: Clean sheet design!
+05.06.2024 16:28:53 - Settings in Sub-Programs will be checked!
+05.06.2024 16:28:53 - * Checking design point:
+05.06.2024 16:28:53 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+05.06.2024 16:28:53 - The in the Setup-Steps selected initialSizing module overwrites them.
+05.06.2024 16:28:53 - ----
+05.06.2024 16:28:53 - * Checking fuselage geometry:
+05.06.2024 16:28:53 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+05.06.2024 16:28:53 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+05.06.2024 16:28:53 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+05.06.2024 16:28:53 - ----
+05.06.2024 16:28:53 - * Checking createMissionXML:
+05.06.2024 16:28:53 - - Design mission will be created.
+05.06.2024 16:28:53 - ----
+05.06.2024 16:28:53 - * Checking wing design:
+05.06.2024 16:28:53 - - Wing geometry available in XML file.
+05.06.2024 16:28:53 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+05.06.2024 16:28:53 - - Existing wing geometry will be overwritten by initialWingSizing module.
+05.06.2024 16:28:53 - ----
+05.06.2024 16:28:53 - * Checking empennage design:
+05.06.2024 16:28:53 - - Tail geometry available in XML file.
+05.06.2024 16:28:53 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+05.06.2024 16:28:53 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+05.06.2024 16:28:53 - ----
+05.06.2024 16:28:53 - * Checking nacelle design and propulsion integration:
+05.06.2024 16:28:53 - - Nacelles already exist.
+05.06.2024 16:28:53 - - Nacelle geometries will be designed by the propulsion integration module.!
+05.06.2024 16:28:53 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+05.06.2024 16:28:53 - ----
+05.06.2024 16:28:53 - * Checking systems design:
+05.06.2024 16:28:53 - - systemsDesign is running in design mode.
+05.06.2024 16:28:53 - ----
+05.06.2024 16:28:53 - * Checking mission analysis:
+05.06.2024 16:28:53 - - missionAnalysis is running in design mode.
+05.06.2024 16:28:53 - ----
+05.06.2024 16:28:53 - * Checking performance calculation:
+05.06.2024 16:28:53 - - Take-off and landing performance are estimated.
+05.06.2024 16:28:53 - - Payload-Range diagram is calculated.
+05.06.2024 16:28:53 - ----
+05.06.2024 16:28:53 - Still to be continued? (y/n)
+05.06.2024 16:28:53 - ----------------------------------------
+05.06.2024 16:28:53 - Setup-Tools ...
+05.06.2024 16:28:53 - Start : initialSizing
+05.06.2024 16:28:53 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+05.06.2024 16:28:53 - ERROR: Error in Setup steps. Error code: 1
+
+05.06.2024 16:28:53 - ---------------------------------------------
+05.06.2024 16:28:53 - Checking Requirements ...
+05.06.2024 16:28:53 - * Checking TLARs ...
+05.06.2024 16:28:53 - * Checking tank volume for design ...
+05.06.2024 16:28:53 - * Checking tank volume for study ...
+05.06.2024 16:28:53 - * Checking reserve fuel ...
+05.06.2024 16:28:53 - * Checking TOM on study mission ...
+05.06.2024 16:28:53 - WARNING: Outputs are written, but may contain errors!
+05.06.2024 16:28:53 - ... calculation finished!
+05.06.2024 16:28:53 - Write output ...
+05.06.2024 16:28:53 - Create Plots ...
+05.06.2024 16:28:53 - Copy Plotting files ...
+05.06.2024 16:28:53 - Write HTML-Report ...
+05.06.2024 16:28:53 - Needed time: 0 min
+05.06.2024 16:28:53 - Finish convergenceLoop
+*******************************************************************************
+05.06.2024 16:28:53 - Start convergenceLoop
+05.06.2024 16:28:53 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+05.06.2024 16:28:53 - Start calculation ...
+05.06.2024 16:28:54 - Design Modus 1: Clean sheet design!
+05.06.2024 16:28:54 - Settings in Sub-Programs will be checked!
+05.06.2024 16:28:54 - * Checking design point:
+05.06.2024 16:28:54 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+05.06.2024 16:28:54 - The in the Setup-Steps selected initialSizing module overwrites them.
+05.06.2024 16:28:54 - ----
+05.06.2024 16:28:54 - * Checking fuselage geometry:
+05.06.2024 16:28:54 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+05.06.2024 16:28:54 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+05.06.2024 16:28:54 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+05.06.2024 16:28:54 - ----
+05.06.2024 16:28:54 - * Checking createMissionXML:
+05.06.2024 16:28:54 - - Design mission will be created.
+05.06.2024 16:28:54 - ----
+05.06.2024 16:28:54 - * Checking wing design:
+05.06.2024 16:28:54 - - Wing geometry available in XML file.
+05.06.2024 16:28:54 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+05.06.2024 16:28:54 - - Existing wing geometry will be overwritten by initialWingSizing module.
+05.06.2024 16:28:54 - ----
+05.06.2024 16:28:54 - * Checking empennage design:
+05.06.2024 16:28:54 - - Tail geometry available in XML file.
+05.06.2024 16:28:54 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+05.06.2024 16:28:54 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+05.06.2024 16:28:54 - ----
+05.06.2024 16:28:54 - * Checking nacelle design and propulsion integration:
+05.06.2024 16:28:54 - - Nacelles already exist.
+05.06.2024 16:28:54 - - Nacelle geometries will be designed by the propulsion integration module.!
+05.06.2024 16:28:54 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+05.06.2024 16:28:54 - ----
+05.06.2024 16:28:54 - * Checking systems design:
+05.06.2024 16:28:54 - - systemsDesign is running in design mode.
+05.06.2024 16:28:54 - ----
+05.06.2024 16:28:54 - * Checking mission analysis:
+05.06.2024 16:28:54 - - missionAnalysis is running in design mode.
+05.06.2024 16:28:54 - ----
+05.06.2024 16:28:54 - * Checking performance calculation:
+05.06.2024 16:28:54 - - Take-off and landing performance are estimated.
+05.06.2024 16:28:54 - - Payload-Range diagram is calculated.
+05.06.2024 16:28:54 - ----
+05.06.2024 16:28:54 - Still to be continued? (y/n)
+05.06.2024 16:28:54 - ----------------------------------------
+05.06.2024 16:28:54 - Setup-Tools ...
+05.06.2024 16:28:54 - Start : initialSizing
+05.06.2024 16:28:54 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+05.06.2024 16:28:54 - ERROR: Error in Setup steps. Error code: 1
+
+05.06.2024 16:28:54 - ---------------------------------------------
+05.06.2024 16:28:54 - Checking Requirements ...
+05.06.2024 16:28:54 - * Checking TLARs ...
+05.06.2024 16:28:54 - * Checking tank volume for design ...
+05.06.2024 16:28:54 - * Checking tank volume for study ...
+05.06.2024 16:28:54 - * Checking reserve fuel ...
+05.06.2024 16:28:54 - * Checking TOM on study mission ...
+05.06.2024 16:28:54 - WARNING: Outputs are written, but may contain errors!
+05.06.2024 16:28:54 - ... calculation finished!
+05.06.2024 16:28:54 - Write output ...
+05.06.2024 16:28:54 - Create Plots ...
+05.06.2024 16:28:54 - Copy Plotting files ...
+05.06.2024 16:28:54 - Write HTML-Report ...
+05.06.2024 16:28:54 - Needed time: 0.0166667 min
+05.06.2024 16:28:54 - Finish convergenceLoop
+*******************************************************************************
+13.06.2024 11:18:16 - Start convergenceLoop
+13.06.2024 11:18:16 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+13.06.2024 11:18:16 - Start calculation ...
+13.06.2024 11:18:16 - Design Modus 1: Clean sheet design!
+13.06.2024 11:18:16 - Settings in Sub-Programs will be checked!
+13.06.2024 11:18:16 - * Checking design point:
+13.06.2024 11:18:16 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+13.06.2024 11:18:16 - The in the Setup-Steps selected initialSizing module overwrites them.
+13.06.2024 11:18:16 - ----
+13.06.2024 11:18:16 - * Checking fuselage geometry:
+13.06.2024 11:18:16 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+13.06.2024 11:18:16 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+13.06.2024 11:18:16 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+13.06.2024 11:18:16 - ----
+13.06.2024 11:18:16 - * Checking createMissionXML:
+13.06.2024 11:18:16 - - Design mission will be created.
+13.06.2024 11:18:16 - ----
+13.06.2024 11:18:16 - * Checking wing design:
+13.06.2024 11:18:16 - - Wing geometry available in XML file.
+13.06.2024 11:18:16 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+13.06.2024 11:18:16 - - Existing wing geometry will be overwritten by initialWingSizing module.
+13.06.2024 11:18:16 - ----
+13.06.2024 11:18:16 - * Checking empennage design:
+13.06.2024 11:18:16 - - Tail geometry available in XML file.
+13.06.2024 11:18:16 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+13.06.2024 11:18:16 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+13.06.2024 11:18:16 - ----
+13.06.2024 11:18:16 - * Checking nacelle design and propulsion integration:
+13.06.2024 11:18:16 - - Nacelles already exist.
+13.06.2024 11:18:16 - - Nacelle geometries will be designed by the propulsion integration module.!
+13.06.2024 11:18:16 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+13.06.2024 11:18:16 - ----
+13.06.2024 11:18:16 - * Checking systems design:
+13.06.2024 11:18:16 - - systemsDesign is running in design mode.
+13.06.2024 11:18:16 - ----
+13.06.2024 11:18:16 - * Checking mission analysis:
+13.06.2024 11:18:16 - - missionAnalysis is running in design mode.
+13.06.2024 11:18:16 - ----
+13.06.2024 11:18:16 - * Checking performance calculation:
+13.06.2024 11:18:16 - - Take-off and landing performance are estimated.
+13.06.2024 11:18:16 - - Payload-Range diagram is calculated.
+13.06.2024 11:18:16 - ----
+13.06.2024 11:18:16 - Still to be continued? (y/n)
+13.06.2024 11:18:16 - ----------------------------------------
+13.06.2024 11:18:16 - Setup-Tools ...
+13.06.2024 11:18:16 - Start : initialSizing
+13.06.2024 11:18:16 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+13.06.2024 11:18:16 - ERROR: Error in Setup steps. Error code: 1
+
+13.06.2024 11:18:16 - ---------------------------------------------
+13.06.2024 11:18:16 - Checking Requirements ...
+13.06.2024 11:18:16 - * Checking TLARs ...
+13.06.2024 11:18:16 - * Checking tank volume for design ...
+13.06.2024 11:18:16 - * Checking tank volume for study ...
+13.06.2024 11:18:16 - * Checking reserve fuel ...
+13.06.2024 11:18:16 - * Checking TOM on study mission ...
+13.06.2024 11:18:16 - WARNING: Outputs are written, but may contain errors!
+13.06.2024 11:18:16 - ... calculation finished!
+13.06.2024 11:18:16 - Write output ...
+13.06.2024 11:18:16 - Create Plots ...
+13.06.2024 11:18:16 - Copy Plotting files ...
+13.06.2024 11:18:16 - Write HTML-Report ...
+13.06.2024 11:18:16 - Needed time: 0 min
+13.06.2024 11:18:17 - Finish convergenceLoop
+*******************************************************************************
+26.07.2024 09:28:51 - Start convergenceLoop
+26.07.2024 09:28:51 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.07.2024 09:28:51 - Start calculation ...
+26.07.2024 09:28:51 - Design Modus 1: Clean sheet design!
+26.07.2024 09:28:51 - Settings in Sub-Programs will be checked!
+26.07.2024 09:28:51 - * Checking design point:
+26.07.2024 09:28:51 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.07.2024 09:28:51 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.07.2024 09:28:51 - ----
+26.07.2024 09:28:51 - * Checking fuselage geometry:
+26.07.2024 09:28:51 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.07.2024 09:28:51 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.07.2024 09:28:51 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.07.2024 09:28:51 - ----
+26.07.2024 09:28:51 - * Checking createMissionXML:
+26.07.2024 09:28:51 - - Design mission will be created.
+26.07.2024 09:28:51 - ----
+26.07.2024 09:28:51 - * Checking wing design:
+26.07.2024 09:28:51 - - Wing geometry available in XML file.
+26.07.2024 09:28:51 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.07.2024 09:28:51 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.07.2024 09:28:51 - ----
+26.07.2024 09:28:51 - * Checking empennage design:
+26.07.2024 09:28:51 - - Tail geometry available in XML file.
+26.07.2024 09:28:51 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.07.2024 09:28:51 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.07.2024 09:28:51 - ----
+26.07.2024 09:28:51 - * Checking nacelle design and propulsion integration:
+26.07.2024 09:28:51 - - Nacelles already exist.
+26.07.2024 09:28:51 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.07.2024 09:28:51 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.07.2024 09:28:51 - ----
+26.07.2024 09:28:51 - * Checking systems design:
+26.07.2024 09:28:51 - - systemsDesign is running in design mode.
+26.07.2024 09:28:51 - ----
+26.07.2024 09:28:51 - * Checking mission analysis:
+26.07.2024 09:28:51 - - missionAnalysis is running in design mode.
+26.07.2024 09:28:51 - ----
+26.07.2024 09:28:51 - * Checking performance calculation:
+26.07.2024 09:28:51 - - Take-off and landing performance are estimated.
+26.07.2024 09:28:51 - - Payload-Range diagram is calculated.
+26.07.2024 09:28:51 - ----
+26.07.2024 09:28:51 - Still to be continued? (y/n)
+26.07.2024 09:28:52 - ----------------------------------------
+26.07.2024 09:28:52 - Setup-Tools ...
+26.07.2024 09:28:52 - Start : initialSizing
+26.07.2024 09:28:52 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.07.2024 09:28:52 - ERROR: Error in Setup steps. Error code: 1
+
+26.07.2024 09:28:52 - ---------------------------------------------
+26.07.2024 09:28:52 - Checking Requirements ...
+26.07.2024 09:28:52 - * Checking TLARs ...
+26.07.2024 09:28:52 - * Checking tank volume for design ...
+26.07.2024 09:28:52 - * Checking tank volume for study ...
+26.07.2024 09:28:52 - * Checking reserve fuel ...
+26.07.2024 09:28:52 - * Checking TOM on study mission ...
+26.07.2024 09:28:52 - WARNING: Outputs are written, but may contain errors!
+26.07.2024 09:28:52 - ... calculation finished!
+26.07.2024 09:28:52 - Write output ...
+26.07.2024 09:28:52 - Create Plots ...
+26.07.2024 09:28:52 - Copy Plotting files ...
+26.07.2024 09:28:52 - Write HTML-Report ...
+26.07.2024 09:28:52 - Needed time: 0.0166667 min
+26.07.2024 09:28:52 - Finish convergenceLoop
+*******************************************************************************
+26.07.2024 09:29:45 - Start convergenceLoop
+26.07.2024 09:29:45 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.07.2024 09:29:45 - Start calculation ...
+26.07.2024 09:29:45 - Design Modus 1: Clean sheet design!
+26.07.2024 09:29:45 - Settings in Sub-Programs will be checked!
+26.07.2024 09:29:45 - * Checking design point:
+26.07.2024 09:29:45 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.07.2024 09:29:45 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.07.2024 09:29:45 - ----
+26.07.2024 09:29:45 - * Checking fuselage geometry:
+26.07.2024 09:29:45 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.07.2024 09:29:45 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.07.2024 09:29:45 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.07.2024 09:29:45 - ----
+26.07.2024 09:29:45 - * Checking createMissionXML:
+26.07.2024 09:29:45 - - Design mission will be created.
+26.07.2024 09:29:45 - ----
+26.07.2024 09:29:45 - * Checking wing design:
+26.07.2024 09:29:45 - - Wing geometry available in XML file.
+26.07.2024 09:29:45 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.07.2024 09:29:45 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.07.2024 09:29:45 - ----
+26.07.2024 09:29:45 - * Checking empennage design:
+26.07.2024 09:29:45 - - Tail geometry available in XML file.
+26.07.2024 09:29:45 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.07.2024 09:29:45 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.07.2024 09:29:45 - ----
+26.07.2024 09:29:45 - * Checking nacelle design and propulsion integration:
+26.07.2024 09:29:45 - - Nacelles already exist.
+26.07.2024 09:29:45 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.07.2024 09:29:45 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.07.2024 09:29:45 - ----
+26.07.2024 09:29:45 - * Checking systems design:
+26.07.2024 09:29:45 - - systemsDesign is running in design mode.
+26.07.2024 09:29:45 - ----
+26.07.2024 09:29:45 - * Checking mission analysis:
+26.07.2024 09:29:45 - - missionAnalysis is running in design mode.
+26.07.2024 09:29:45 - ----
+26.07.2024 09:29:45 - * Checking performance calculation:
+26.07.2024 09:29:45 - - Take-off and landing performance are estimated.
+26.07.2024 09:29:45 - - Payload-Range diagram is calculated.
+26.07.2024 09:29:45 - ----
+26.07.2024 09:29:45 - Still to be continued? (y/n)
+26.07.2024 09:29:45 - ----------------------------------------
+26.07.2024 09:29:45 - Setup-Tools ...
+26.07.2024 09:29:45 - Start : initialSizing
+26.07.2024 09:29:45 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.07.2024 09:29:45 - ERROR: Error in Setup steps. Error code: 1
+
+26.07.2024 09:29:45 - ---------------------------------------------
+26.07.2024 09:29:45 - Checking Requirements ...
+26.07.2024 09:29:45 - * Checking TLARs ...
+26.07.2024 09:29:45 - * Checking tank volume for design ...
+26.07.2024 09:29:45 - * Checking tank volume for study ...
+26.07.2024 09:29:45 - * Checking reserve fuel ...
+26.07.2024 09:29:45 - * Checking TOM on study mission ...
+26.07.2024 09:29:45 - WARNING: Outputs are written, but may contain errors!
+26.07.2024 09:29:45 - ... calculation finished!
+26.07.2024 09:29:45 - Write output ...
+26.07.2024 09:29:45 - Create Plots ...
+26.07.2024 09:29:45 - Copy Plotting files ...
+26.07.2024 09:29:45 - Write HTML-Report ...
+26.07.2024 09:29:45 - Needed time: 0 min
+26.07.2024 09:29:45 - Finish convergenceLoop
+*******************************************************************************
+26.07.2024 09:30:22 - Start convergenceLoop
+26.07.2024 09:30:22 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.07.2024 09:30:22 - Start calculation ...
+26.07.2024 09:30:22 - Design Modus 1: Clean sheet design!
+26.07.2024 09:30:22 - Settings in Sub-Programs will be checked!
+26.07.2024 09:30:22 - * Checking design point:
+26.07.2024 09:30:22 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.07.2024 09:30:22 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.07.2024 09:30:22 - ----
+26.07.2024 09:30:22 - * Checking fuselage geometry:
+26.07.2024 09:30:22 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.07.2024 09:30:22 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.07.2024 09:30:22 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.07.2024 09:30:22 - ----
+26.07.2024 09:30:22 - * Checking createMissionXML:
+26.07.2024 09:30:22 - - Design mission will be created.
+26.07.2024 09:30:22 - ----
+26.07.2024 09:30:22 - * Checking wing design:
+26.07.2024 09:30:22 - - Wing geometry available in XML file.
+26.07.2024 09:30:22 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.07.2024 09:30:22 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.07.2024 09:30:22 - ----
+26.07.2024 09:30:22 - * Checking empennage design:
+26.07.2024 09:30:22 - - Tail geometry available in XML file.
+26.07.2024 09:30:22 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.07.2024 09:30:22 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.07.2024 09:30:22 - ----
+26.07.2024 09:30:22 - * Checking nacelle design and propulsion integration:
+26.07.2024 09:30:22 - - Nacelles already exist.
+26.07.2024 09:30:22 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.07.2024 09:30:22 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.07.2024 09:30:22 - ----
+26.07.2024 09:30:22 - * Checking systems design:
+26.07.2024 09:30:22 - - systemsDesign is running in design mode.
+26.07.2024 09:30:22 - ----
+26.07.2024 09:30:22 - * Checking mission analysis:
+26.07.2024 09:30:22 - - missionAnalysis is running in design mode.
+26.07.2024 09:30:22 - ----
+26.07.2024 09:30:22 - * Checking performance calculation:
+26.07.2024 09:30:22 - - Take-off and landing performance are estimated.
+26.07.2024 09:30:22 - - Payload-Range diagram is calculated.
+26.07.2024 09:30:22 - ----
+26.07.2024 09:30:22 - Still to be continued? (y/n)
+26.07.2024 09:30:22 - ----------------------------------------
+26.07.2024 09:30:22 - Setup-Tools ...
+26.07.2024 09:30:22 - Start : fuselageDesign
+26.07.2024 09:30:37 - Start : initialSizing
+26.07.2024 09:30:37 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.07.2024 09:30:37 - ERROR: Error in Setup steps. Error code: 1
+
+26.07.2024 09:30:37 - ---------------------------------------------
+26.07.2024 09:30:37 - Checking Requirements ...
+26.07.2024 09:30:37 - * Checking TLARs ...
+26.07.2024 09:30:37 - * Checking tank volume for design ...
+26.07.2024 09:30:37 - * Checking tank volume for study ...
+26.07.2024 09:30:37 - * Checking reserve fuel ...
+26.07.2024 09:30:37 - * Checking TOM on study mission ...
+26.07.2024 09:30:37 - WARNING: Outputs are written, but may contain errors!
+26.07.2024 09:30:37 - ... calculation finished!
+26.07.2024 09:30:37 - Write output ...
+26.07.2024 09:30:37 - Create Plots ...
+26.07.2024 09:30:37 - Copy Plotting files ...
+26.07.2024 09:30:37 - Write HTML-Report ...
+26.07.2024 09:30:37 - Needed time: 0.25 min
+26.07.2024 09:30:37 - Finish convergenceLoop
+*******************************************************************************
+26.07.2024 09:30:37 - Start convergenceLoop
+26.07.2024 09:30:37 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.07.2024 09:30:37 - Start calculation ...
+26.07.2024 09:30:37 - Design Modus 1: Clean sheet design!
+26.07.2024 09:30:37 - Settings in Sub-Programs will be checked!
+26.07.2024 09:30:37 - * Checking design point:
+26.07.2024 09:30:37 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.07.2024 09:30:37 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.07.2024 09:30:37 - ----
+26.07.2024 09:30:37 - * Checking fuselage geometry:
+26.07.2024 09:30:37 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.07.2024 09:30:37 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.07.2024 09:30:37 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.07.2024 09:30:37 - ----
+26.07.2024 09:30:37 - * Checking createMissionXML:
+26.07.2024 09:30:37 - - Design mission will be created.
+26.07.2024 09:30:37 - ----
+26.07.2024 09:30:37 - * Checking wing design:
+26.07.2024 09:30:37 - - Wing geometry available in XML file.
+26.07.2024 09:30:37 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.07.2024 09:30:37 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.07.2024 09:30:37 - ----
+26.07.2024 09:30:37 - * Checking empennage design:
+26.07.2024 09:30:37 - - Tail geometry available in XML file.
+26.07.2024 09:30:37 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.07.2024 09:30:37 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.07.2024 09:30:37 - ----
+26.07.2024 09:30:37 - * Checking nacelle design and propulsion integration:
+26.07.2024 09:30:37 - - Nacelles already exist.
+26.07.2024 09:30:37 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.07.2024 09:30:37 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.07.2024 09:30:37 - ----
+26.07.2024 09:30:37 - * Checking systems design:
+26.07.2024 09:30:37 - - systemsDesign is running in design mode.
+26.07.2024 09:30:37 - ----
+26.07.2024 09:30:37 - * Checking mission analysis:
+26.07.2024 09:30:37 - - missionAnalysis is running in design mode.
+26.07.2024 09:30:37 - ----
+26.07.2024 09:30:37 - * Checking performance calculation:
+26.07.2024 09:30:37 - - Take-off and landing performance are estimated.
+26.07.2024 09:30:37 - - Payload-Range diagram is calculated.
+26.07.2024 09:30:37 - ----
+26.07.2024 09:30:37 - Still to be continued? (y/n)
+26.07.2024 09:30:37 - ----------------------------------------
+26.07.2024 09:30:37 - Setup-Tools ...
+26.07.2024 09:30:37 - Start : fuselageDesign
+26.07.2024 09:30:42 - Start : initialSizing
+26.07.2024 09:30:42 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.07.2024 09:30:42 - ERROR: Error in Setup steps. Error code: 1
+
+26.07.2024 09:30:42 - ---------------------------------------------
+26.07.2024 09:30:42 - Checking Requirements ...
+26.07.2024 09:30:42 - * Checking TLARs ...
+26.07.2024 09:30:42 - * Checking tank volume for design ...
+26.07.2024 09:30:42 - * Checking tank volume for study ...
+26.07.2024 09:30:42 - * Checking reserve fuel ...
+26.07.2024 09:30:42 - * Checking TOM on study mission ...
+26.07.2024 09:30:42 - WARNING: Outputs are written, but may contain errors!
+26.07.2024 09:30:42 - ... calculation finished!
+26.07.2024 09:30:42 - Write output ...
+26.07.2024 09:30:42 - Create Plots ...
+26.07.2024 09:30:42 - Copy Plotting files ...
+26.07.2024 09:30:42 - Write HTML-Report ...
+26.07.2024 09:30:42 - Needed time: 0.0833333 min
+26.07.2024 09:30:42 - Finish convergenceLoop
+*******************************************************************************
+26.07.2024 09:31:45 - Start convergenceLoop
+26.07.2024 09:31:45 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.07.2024 09:31:45 - Start calculation ...
+26.07.2024 09:31:45 - Design Modus 1: Clean sheet design!
+26.07.2024 09:31:45 - Settings in Sub-Programs will be checked!
+26.07.2024 09:31:45 - * Checking design point:
+26.07.2024 09:31:45 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.07.2024 09:31:45 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.07.2024 09:31:45 - ----
+26.07.2024 09:31:45 - * Checking fuselage geometry:
+26.07.2024 09:31:45 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.07.2024 09:31:45 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.07.2024 09:31:45 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.07.2024 09:31:45 - ----
+26.07.2024 09:31:45 - * Checking createMissionXML:
+26.07.2024 09:31:45 - - Design mission will be created.
+26.07.2024 09:31:45 - ----
+26.07.2024 09:31:45 - * Checking wing design:
+26.07.2024 09:31:45 - - Wing geometry available in XML file.
+26.07.2024 09:31:45 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.07.2024 09:31:45 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.07.2024 09:31:45 - ----
+26.07.2024 09:31:45 - * Checking empennage design:
+26.07.2024 09:31:45 - - Tail geometry available in XML file.
+26.07.2024 09:31:45 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.07.2024 09:31:45 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.07.2024 09:31:45 - ----
+26.07.2024 09:31:45 - * Checking nacelle design and propulsion integration:
+26.07.2024 09:31:45 - - Nacelles already exist.
+26.07.2024 09:31:45 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.07.2024 09:31:45 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.07.2024 09:31:45 - ----
+26.07.2024 09:31:45 - * Checking systems design:
+26.07.2024 09:31:45 - - systemsDesign is running in design mode.
+26.07.2024 09:31:45 - ----
+26.07.2024 09:31:45 - * Checking mission analysis:
+26.07.2024 09:31:45 - - missionAnalysis is running in design mode.
+26.07.2024 09:31:45 - ----
+26.07.2024 09:31:45 - * Checking performance calculation:
+26.07.2024 09:31:45 - - Take-off and landing performance are estimated.
+26.07.2024 09:31:45 - - Payload-Range diagram is calculated.
+26.07.2024 09:31:45 - ----
+26.07.2024 09:31:45 - Still to be continued? (y/n)
+26.07.2024 09:31:45 - ----------------------------------------
+26.07.2024 09:31:45 - Setup-Tools ...
+26.07.2024 09:31:45 - Start : initialSizing
+26.07.2024 09:31:46 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.07.2024 09:31:46 - ERROR: Error in Setup steps. Error code: 1
+
+26.07.2024 09:31:46 - ---------------------------------------------
+26.07.2024 09:31:46 - Checking Requirements ...
+26.07.2024 09:31:46 - * Checking TLARs ...
+26.07.2024 09:31:46 - * Checking tank volume for design ...
+26.07.2024 09:31:46 - * Checking tank volume for study ...
+26.07.2024 09:31:46 - * Checking reserve fuel ...
+26.07.2024 09:31:46 - * Checking TOM on study mission ...
+26.07.2024 09:31:46 - WARNING: Outputs are written, but may contain errors!
+26.07.2024 09:31:46 - ... calculation finished!
+26.07.2024 09:31:46 - Write output ...
+26.07.2024 09:31:46 - Create Plots ...
+26.07.2024 09:31:46 - Copy Plotting files ...
+26.07.2024 09:31:46 - Write HTML-Report ...
+26.07.2024 09:31:46 - Needed time: 0.0166667 min
+26.07.2024 09:31:46 - Finish convergenceLoop
+*******************************************************************************
+26.07.2024 12:37:56 - Start convergenceLoop
+26.07.2024 12:37:56 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.07.2024 12:37:56 - Start calculation ...
+26.07.2024 12:37:56 - Design Modus 1: Clean sheet design!
+26.07.2024 12:37:56 - Settings in Sub-Programs will be checked!
+26.07.2024 12:37:56 - * Checking design point:
+26.07.2024 12:37:56 - - CRITICAL: Values for W/S and T/W or P/W are already entered.
+26.07.2024 12:37:56 - The in the Setup-Steps selected initialSizing module overwrites them.
+26.07.2024 12:37:56 - ----
+26.07.2024 12:37:56 - * Checking fuselage geometry:
+26.07.2024 12:37:56 - - Fuselage geometry available and fuselageDesign module activated in the Setup-Steps.
+26.07.2024 12:37:56 - - Fuselage geometry will not be overwritten by fuselageDesign module (see corresponding switch in its config file).
+26.07.2024 12:37:56 - - CRITICAL: This can lead to inconsistencies between certain accommodation data and the existing fuselage geometry.!
+26.07.2024 12:37:56 - ----
+26.07.2024 12:37:56 - * Checking createMissionXML:
+26.07.2024 12:37:56 - - Design mission will be created.
+26.07.2024 12:37:56 - ----
+26.07.2024 12:37:56 - * Checking wing design:
+26.07.2024 12:37:56 - - Wing geometry available in XML file.
+26.07.2024 12:37:56 - - Switch for initialWingSizing in config of wingDesign tool is activated.
+26.07.2024 12:37:56 - - Existing wing geometry will be overwritten by initialWingSizing module.
+26.07.2024 12:37:56 - ----
+26.07.2024 12:37:56 - * Checking empennage design:
+26.07.2024 12:37:56 - - Tail geometry available in XML file.
+26.07.2024 12:37:56 - - Switch for initialTailSizing in config of empennageSizing tool is activated.
+26.07.2024 12:37:56 - - ATTENTION: Existing tail geometry will be overwritten by empennageSizing module.
+26.07.2024 12:37:56 - ----
+26.07.2024 12:37:56 - * Checking nacelle design and propulsion integration:
+26.07.2024 12:37:56 - - Nacelles already exist.
+26.07.2024 12:37:56 - - Nacelle geometries will be designed by the propulsion integration module.!
+26.07.2024 12:37:56 - - CRITICAL: Existing nacelle geometries will be overwritten by the propulsion integration module.!
+26.07.2024 12:37:56 - ----
+26.07.2024 12:37:56 - * Checking systems design:
+26.07.2024 12:37:56 - - systemsDesign is running in design mode.
+26.07.2024 12:37:56 - ----
+26.07.2024 12:37:56 - * Checking mission analysis:
+26.07.2024 12:37:56 - - missionAnalysis is running in design mode.
+26.07.2024 12:37:56 - ----
+26.07.2024 12:37:56 - * Checking performance calculation:
+26.07.2024 12:37:56 - - Take-off and landing performance are estimated.
+26.07.2024 12:37:56 - - Payload-Range diagram is calculated.
+26.07.2024 12:37:56 - ----
+26.07.2024 12:37:56 - Still to be continued? (y/n)
+26.07.2024 12:37:56 - ----------------------------------------
+26.07.2024 12:37:56 - Setup-Tools ...
+26.07.2024 12:37:56 - Start : initialSizing
+26.07.2024 12:37:57 - ERROR: Tool-Execution: Error code 1 in Program initialSizing
+26.07.2024 12:37:57 - ERROR: Error in Setup steps. Error code: 1
+
+26.07.2024 12:37:57 - ---------------------------------------------
+26.07.2024 12:37:57 - Checking Requirements ...
+26.07.2024 12:37:57 - * Checking TLARs ...
+26.07.2024 12:37:57 - * Checking tank volume for design ...
+26.07.2024 12:37:57 - * Checking tank volume for study ...
+26.07.2024 12:37:57 - * Checking reserve fuel ...
+26.07.2024 12:37:57 - * Checking TOM on study mission ...
+26.07.2024 12:37:57 - WARNING: Outputs are written, but may contain errors!
+26.07.2024 12:37:57 - ... calculation finished!
+26.07.2024 12:37:57 - Write output ...
+26.07.2024 12:37:57 - Create Plots ...
+26.07.2024 12:37:57 - Copy Plotting files ...
+26.07.2024 12:37:57 - Write HTML-Report ...
+26.07.2024 12:37:57 - Needed time: 0.0166667 min
+26.07.2024 12:37:57 - Finish convergenceLoop
diff --git a/UnicadoGUI/Backend/output_files/logFiles/createMissionXML.log b/UnicadoGUI/Backend/output_files/logFiles/createMissionXML.log
new file mode 100644
index 0000000000000000000000000000000000000000..22ee76ed8e2651e1a816757e390fb6b446b9e701
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/logFiles/createMissionXML.log
@@ -0,0 +1,10 @@
+*******************************************************************************
+22.01.2024 11:07:02 - Start createMissionXML
+22.01.2024 11:07:02 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.01.2024 11:07:02 - Start calculation ...
+22.01.2024 11:07:02 - ... calculation finished!
+22.01.2024 11:07:02 - Create missionDesign.xml...
+22.01.2024 11:07:02 - Create missionReq.xml...
+22.01.2024 11:07:02 - Write output ...
+22.01.2024 11:07:02 - Write XML-Output ...
+22.01.2024 11:07:02 - Finish createMissionXML
diff --git a/UnicadoGUI/Backend/output_files/logFiles/empennageSizing.log b/UnicadoGUI/Backend/output_files/logFiles/empennageSizing.log
new file mode 100644
index 0000000000000000000000000000000000000000..857867a05e1c4cff75d5a3d30afcff592dfba484
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/logFiles/empennageSizing.log
@@ -0,0 +1,16 @@
+*******************************************************************************
+22.01.2024 11:07:02 - Start empennageSizing
+22.01.2024 11:07:02 - Create: MainWing ...
+22.01.2024 11:07:02 - Create: Stabiliser ...
+22.01.2024 11:07:02 - Create: Fin ...
+22.01.2024 11:07:02 - Create: Fuselage ...
+22.01.2024 11:07:02 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.01.2024 11:07:02 - Start calculation...
+22.01.2024 11:07:02 - Scaling Modus 2:
+22.01.2024 11:07:02 - WARNING: Matched-switch for fin in Acft-XML off. Volume coefficient is determined from current geometry. Then resizing method ("mySettingsPt->tailSizingMode"=2) is executed.! ATTENTION: Can lead to errors with large geometry changes in other programs (e.g. fuselageDesign, wingDesign).!
+22.01.2024 11:07:02 - WARNING: Matched-switch for tailplane in Acft-XML off. Volume coefficient is determined from current geometry. Then resizing method ("mySettingsPt->tailSizingMode"=2) is executed.! ATTENTION: Can lead to errors with large geometry changes in other programs (e.g. fuselageDesign, wingDesign).!
+22.01.2024 11:07:02 - Writing output...
+22.01.2024 11:07:02 - Write XML-Output ...
+22.01.2024 11:07:02 - Write HTML-Report ...
+22.01.2024 11:07:02 - Write TeX-Report ...
+22.01.2024 11:07:02 - Finish empennageSizing
diff --git a/UnicadoGUI/Backend/output_files/logFiles/engineSizing.log b/UnicadoGUI/Backend/output_files/logFiles/engineSizing.log
new file mode 100644
index 0000000000000000000000000000000000000000..32366bee663293c5beb059e7b78daca9644dd760
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/logFiles/engineSizing.log
@@ -0,0 +1,17 @@
+*******************************************************************************
+22.01.2024 11:07:03 - Start engineSizing
+22.01.2024 11:07:03 - Engine geometry will be scaled (engineScalingMode: 1).
+22.01.2024 11:07:03 - Auto selected engine is: V2527-A5
+22.01.2024 11:07:03 - Check existence of directory for engine decks: ..\projects\CSR\CSR-02\engineData\V2527-A5\: Directory existing.
+22.01.2024 11:07:03 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.01.2024 11:07:03 - Start calculation ...
+22.01.2024 11:07:03 - Required thrust scaling factor (for T/W): 1.16042
+22.01.2024 11:07:05 - Unscaled SLST = 110.31 kN
+22.01.2024 11:07:05 - Unscaled SLST from Deck = 110.31 kN
+22.01.2024 11:07:05 - Scaled SLST = 128.01 kN
+22.01.2024 11:07:05 - ... calculation finished!
+22.01.2024 11:07:05 - Write output ...
+22.01.2024 11:07:05 - Write XML-Output ...
+22.01.2024 11:07:05 - Write HTML-Report ...
+22.01.2024 11:07:05 - Write TeX-Report ...
+22.01.2024 11:07:05 - Finish engineSizing
diff --git a/UnicadoGUI/Backend/output_files/logFiles/fuselageDesign.log b/UnicadoGUI/Backend/output_files/logFiles/fuselageDesign.log
new file mode 100644
index 0000000000000000000000000000000000000000..30c42f750eae53832d21466fa85c135b9aa233c7
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/logFiles/fuselageDesign.log
@@ -0,0 +1,16 @@
+*******************************************************************************
+26.07.2024 09:30:37 - Start fuselageDesign
+
+26.07.2024 09:30:37 - Importing the configuration file ...
+
+26.07.2024 09:30:37 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.07.2024 09:30:37 - Start calculation ...
+26.07.2024 09:30:38 - WARNING: Compartment 'aft' is in front of wing box. Moving compartment behind wing box automatically.
+26.07.2024 09:30:38 - ... calculation finished!
+26.07.2024 09:30:38 - Write output ...
+26.07.2024 09:30:38 - Write XML-Output ...
+26.07.2024 09:30:38 - Create Plots ...
+26.07.2024 09:30:42 - Copy Plotting files ...
+26.07.2024 09:30:42 - Write HTML-Report ...
+26.07.2024 09:30:42 - Write TeX-Report ...
+26.07.2024 09:30:42 - Finish fuselageDesign
diff --git a/UnicadoGUI/Backend/output_files/logFiles/initialSizing.log b/UnicadoGUI/Backend/output_files/logFiles/initialSizing.log
new file mode 100644
index 0000000000000000000000000000000000000000..170e2213e40c3ad605f00594da693c412c99dd69
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/logFiles/initialSizing.log
@@ -0,0 +1,24 @@
+*******************************************************************************
+26.07.2024 12:37:57 - Start initialSizing
+26.07.2024 12:37:57 - Executing Mode 0: Normal execution mode.
+26.07.2024 12:37:57 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+26.07.2024 12:37:57 - Start calculation ...
+26.07.2024 12:37:57 - Calculation Mode: JET
+26.07.2024 12:37:57 - - Initialize Jet-Engine ...
+26.07.2024 12:37:57 - - Estimation of lift coefficients ...
+26.07.2024 12:37:57 - - Estimation of zero-lift drag in cruise configuration ...
+26.07.2024 12:37:57 - - Calculation of required W/S for landing ...
+26.07.2024 12:37:57 - - Calculation of required T/W to meet climb requirement ...
+26.07.2024 12:37:57 - - Calculation of critical design points...
+26.07.2024 12:37:57 - - Start calculation of empty mass and takeoff mass ...
+26.07.2024 12:37:57 - **** FINAL VALUES ****
+26.07.2024 12:37:57 - * W/S = 625.837
+26.07.2024 12:37:57 - * T/W = 0.332061
+26.07.2024 12:37:57 - * OME = 50088.4
+26.07.2024 12:37:57 - * MTOM = 83192
+26.07.2024 12:37:57 - **** Jet calculation done. ****
+26.07.2024 12:37:57 - ... calculation finished!
+26.07.2024 12:37:57 - Write output ...
+26.07.2024 12:37:57 - Write XML-Output ...
+26.07.2024 12:37:57 - ERROR: tool level to low (value) ..\projects\CSR\CSR-02\CSR-02.xml/AcftExchangeFile/MassesAndLoadings/MTOM
+26.07.2024 12:37:57 - Finish initialSizing
diff --git a/UnicadoGUI/Backend/output_files/logFiles/landingGearDesign.log b/UnicadoGUI/Backend/output_files/logFiles/landingGearDesign.log
new file mode 100644
index 0000000000000000000000000000000000000000..d08a56f9599c58693ad92ad0e7b002cc7a98ebed
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/logFiles/landingGearDesign.log
@@ -0,0 +1,40 @@
+*******************************************************************************
+22.01.2024 11:07:05 - Start landingGearDesign
+22.01.2024 11:07:05 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.01.2024 11:07:05 - Create: MainWing ...
+22.01.2024 11:07:05 - Create: Stabiliser ...
+22.01.2024 11:07:05 - Create: Fin ...
+22.01.2024 11:07:05 - Create: Fuselage ...
+22.01.2024 11:07:05 - Create: InnerRightWingNacelle ...
+22.01.2024 11:07:05 - Create: InnerLeftWingNacelle ...
+22.01.2024 11:07:05 - Create: NoseGear ...
+22.01.2024 11:07:05 - Create: OuterRightMainGear ...
+22.01.2024 11:07:05 - Create: OuterLeftMainGear ...
+22.01.2024 11:07:05 - Start calculation ...
+22.01.2024 11:07:05 - WARNING: Track width requirements cannot be met:
+22.01.2024 11:07:05 - MinTrackforRetractability = 0m
+22.01.2024 11:07:05 - MinTrackStability = 9.8851m
+22.01.2024 11:07:05 - MaxTrackTurningRadius = 13.9928m
+22.01.2024 11:07:05 - MaxTrackNacelle = 8.4991m
+22.01.2024 11:07:05 - WARNING: Low stability since
+22.01.2024 11:07:05 - Min track needed for stability = 9.8851m
+22.01.2024 11:07:05 - Max track limited by Nacelle = 8.4991m
+22.01.2024 11:07:05 - WARNING: Track width requirements cannot be met:
+22.01.2024 11:07:05 - MinTrackforRetractability = 0m
+22.01.2024 11:07:05 - MinTrackStability = 9.88437m
+22.01.2024 11:07:05 - MaxTrackTurningRadius = 13.9937m
+22.01.2024 11:07:05 - MaxTrackNacelle = 8.4991m
+22.01.2024 11:07:05 - WARNING: Low stability since
+22.01.2024 11:07:05 - Min track needed for stability = 9.88437m
+22.01.2024 11:07:05 - Max track limited by Nacelle = 8.4991m
+22.01.2024 11:07:05 - WARNING: CAUTION: Unstable chassis, nose gear position critical
+22.01.2024 11:07:05 - WARNING: CAUTION: Minimum pitch angle of 15 deg is not reached, main gear position critical
+22.01.2024 11:07:05 - ... calculation finished!
+22.01.2024 11:07:05 - Write output ...
+22.01.2024 11:07:05 - Write XML-Output ...
+22.01.2024 11:07:05 - Write NoseGear in XML file
+22.01.2024 11:07:05 - Write OuterRightMainGear in XML file
+22.01.2024 11:07:05 - Write OuterLeftMainGear in XML file
+22.01.2024 11:07:05 - Write HTML-Report ...
+22.01.2024 11:07:05 - Write TeX-Report ...
+22.01.2024 11:07:05 - Finish landingGearDesign
diff --git a/UnicadoGUI/Backend/output_files/logFiles/propulsionIntegration.log b/UnicadoGUI/Backend/output_files/logFiles/propulsionIntegration.log
new file mode 100644
index 0000000000000000000000000000000000000000..b078a65e6571d2c6f8f707b737616990bd4f3bd1
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/logFiles/propulsionIntegration.log
@@ -0,0 +1,32 @@
+*******************************************************************************
+22.01.2024 11:07:05 - Start propulsionIntegration
+22.01.2024 11:07:05 - Nacelle sizing mode 2 activated: Rescaling of nacelles.
+22.01.2024 11:07:05 - Pylon sizing mode 1 activated: Pylons will be sized.
+22.01.2024 11:07:05 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.01.2024 11:07:05 - Create: MainWing ...
+22.01.2024 11:07:05 - Create: Stabiliser ...
+22.01.2024 11:07:05 - Create: Fin ...
+22.01.2024 11:07:05 - Create: Fuselage ...
+22.01.2024 11:07:05 - Create: InnerRightWingNacelle ...
+22.01.2024 11:07:05 - Create: InnerLeftWingNacelle ...
+22.01.2024 11:07:05 - Start calculation ...
+22.01.2024 11:07:05 - Start of engine integration...
+22.01.2024 11:07:05 - So far no scaling of the nacelles occurred!
+22.01.2024 11:07:05 - Save reference values ...
+22.01.2024 11:07:05 - Integration of the engines was successful!
+22.01.2024 11:07:05 - Start of pylon design...
+22.01.2024 11:07:05 - ... Design of pylon number: 1
+22.01.2024 11:07:05 - ... Pylon mode: Sizing...
+22.01.2024 11:07:05 - ... Pylon sizing with beforehand designed nacelle geometry...
+22.01.2024 11:07:05 - ... Design of pylon number: 2
+22.01.2024 11:07:05 - ... Pylon mode: Sizing...
+22.01.2024 11:07:05 - ... Pylon sizing with beforehand designed nacelle geometry...
+22.01.2024 11:07:05 - Number of designed pylons: 2
+22.01.2024 11:07:05 - Design of the pylons was successful!
+22.01.2024 11:07:05 - ... calculation finished!
+22.01.2024 11:07:05 - Write output ...
+22.01.2024 11:07:05 - Write XML-Output ...
+22.01.2024 11:07:05 - Write reference values for nacelle scaling in aircraft xml
+22.01.2024 11:07:05 - Write HTML-Report ...
+22.01.2024 11:07:05 - Write TeX-Report ...
+22.01.2024 11:07:05 - Finish propulsionIntegration
diff --git a/UnicadoGUI/Backend/output_files/logFiles/wingDesign.log b/UnicadoGUI/Backend/output_files/logFiles/wingDesign.log
new file mode 100644
index 0000000000000000000000000000000000000000..df9077d5ca64cea1a97904a07f415e83c114f75e
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/logFiles/wingDesign.log
@@ -0,0 +1,20 @@
+*******************************************************************************
+22.01.2024 11:07:02 - Start wingDesign
+22.01.2024 11:07:02 - Use file: ..\projects\CSR\CSR-02\CSR-02.xml
+22.01.2024 11:07:02 - Generating: Fuselage ...
+22.01.2024 11:07:02 - Start calculation ...
+22.01.2024 11:07:02 - * Generate: MainWing ...
+22.01.2024 11:07:02 - Analyze existing geometry ...
+22.01.2024 11:07:02 - Program-Execution Mode 2: Wing-Modifier ...
+22.01.2024 11:07:02 - Execute area scaling (mode 1)...
+22.01.2024 11:07:02 - Set wing reference point to [12.5273, 0, -1.27368].
+22.01.2024 11:07:02 - Scaling tank volume with factor 1
+22.01.2024 11:07:02 - Required tank volume: 40991.9 liters.
+22.01.2024 11:07:02 - Refueling wings ...
+22.01.2024 11:07:02 - Refueling centre tank ...
+22.01.2024 11:07:02 - ... calculation finished!
+22.01.2024 11:07:02 - Write output ...
+22.01.2024 11:07:02 - Write XML-Output ...
+22.01.2024 11:07:02 - Write HTML-Report ...
+22.01.2024 11:07:02 - Write TeX-Report ...
+22.01.2024 11:07:02 - Finish wingDesign
diff --git a/UnicadoGUI/Backend/output_files/reportHTML/convergenceLoop_report.html b/UnicadoGUI/Backend/output_files/reportHTML/convergenceLoop_report.html
new file mode 100644
index 0000000000000000000000000000000000000000..3a5622a2e789e9d62510f0b453acb94aa79f969d
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/reportHTML/convergenceLoop_report.html
@@ -0,0 +1,323 @@
+<!DOCTYPE html PUBLIC "-//W3C//DTD XHTML 1.0 Transitional//EN"
+ "http://www.w3.org/TR/xhtml1/DTD/xhtml1-transitional.dtd">
+<html xmlns="http://www.w3.org/1999/xhtml">
+<head>
+<meta http-equiv="content-type" content="text/html; charset=ISO-8859-1"/>
+<title>convergenceLoop CeRAS-CSR-02</title>
+<style type="text/css">
+body,td,a,p{font-family:Times,sans-serif;font-size:12pt}
+h1{font-family:Times,sans-serif;font-size:14pt}
+h2{font-family:Times,sans-serif;font-size:12pt}
+body{color:#333;margin:15px;background:#fff;}
+table,img{border:0;max-width:100%}
+td,th{padding:5px;margin:5px}
+.ceras{width:100%}
+.ceras2Col{width:200%}
+#wrapper{width:100%;margin-bottom:1em;float:left}
+#leftCol{width:47.5%;float:left;margin-bottom:2em;}
+#rightCol{width:47.5%;margin-left:52.5%;margin-bottom:2em;}
+</style>
+</head>
+<body>
+<h1>Report of convergenceLoop: CeRAS-CSR-02</h1>
+<!-- Begin CeRAS Report -->
+<!-- ################################################################################################### -->
+<div id="wrapper">
+<h2>MTOM Convergence</h2>
+<div id="leftCol">
+<table class="ceras">
+<colgroup>
+<col/>
+<col width="50%"/>
+</colgroup>
+<tr>
+<td>Convergence successful </td><td></td>
+</tr>
+<tr>
+<td>Postprocessing not successful </td><td></td>
+</tr>
+<tr>
+<td>Needed time</td><td>0.02 min</td>
+</tr>
+<tr>
+<td>Number of iterations</td><td>1</td>
+</tr>
+</table>
+<br/>
+<h2>Key A/C Characteristics</h2>
+<table class="ceras">
+<colgroup>
+<col/>
+<col width="50%"/>
+</colgroup>
+<tr>
+<td>MTOM [kg]:</td><td>78619.9</td>
+</tr>
+<tr>
+<td>OME [kg]:</td><td>42154.3</td>
+</tr>
+</table>
+<h2>Check tank volume</h2>
+<table class="ceras">
+<colgroup>
+<col/>
+<col width="50%"/>
+</colgroup>
+<tr>
+<td>Max. Usable Fuel [kg]:</td><td>32177.4</td>
+</tr>
+<tr>
+<td>Loaded Fuel on Design Mission [kg]:</td><td>19566.5</td>
+</tr>
+</table>
+<br/>
+</div>
+</div>
+<div id="wrapper">
+<table class="ceras2Col" border="1" rules="groups">
+<colgroup>
+<col/>
+<col width="10%"/>
+<col width="10%"/>
+<col width="5%"/>
+<col width="15%"/>
+<col width="5%"/>
+<col width="5%"/>
+<col width="10%"/>
+</colgroup>
+<thead align="left">
+<tr>
+<th>TLAR</th> <th>Unit</th> <th>Requirement</th> <th>Calc</th> <th>Rel. Change [%]</th> <th>Fulfilled</th> <th>Checked</th> <th>Recommendation</th>
+</tr>
+</thead>
+<tbody>
+<tr>
+<td> Balanced Field Length (BFL) <br/> @ SL, MTOM, ISA+0-Conditions </td><td> m </td><td>< 2122</td><td>0</td><td>-100</td><td>1</td><td>0</td><td> </td>
+</tr>
+<tr>
+<td> Landing distance (LDN) <br/> @ MLM, SL, ISA+0 </td><td> m </td><td>< 2387</td><td>1353.28</td><td>-43.31</td><td>1</td><td>0</td><td> </td>
+</tr>
+<tr>
+<td> Approach speed (v_app) </td><td> KCAS </td><td>< 138</td><td>128.745</td><td>-6.71</td><td>1</td><td>0</td><td> </td>
+</tr>
+<tr>
+<td> </td><td> </td><td> </td><td> </td><td> </td><td> </td><td> </td><td> </td>
+</tr>
+<tr>
+<td> Initial Cruise Altitude (ICA) <br/> after T/O @ MTOM, ISA+0 </td><td> ft </td><td>33000</td><td>33000</td><td>0</td><td>1</td><td>0</td><td> </td>
+</tr>
+<tr>
+<td> Time-to-climb (TTC) <br/> after T/O @ MTOM, ISA+0 (from 1500 ft to ICA) </td><td> min </td><td>< 35</td><td>15.83</td><td>-54.77</td><td>1</td><td>0</td><td> </td>
+</tr>
+<tr>
+<td> Max. operating (cruise) altitude <br/> Climb with 100 ft/min @ ISA+0 </td><td> ft </td><td>> 38500</td><td>35000 <br/>(38790.1)</td><td>0.75</td><td>1</td><td>0</td><td> </td>
+</tr>
+<tr>
+<td> Max. ceiling <br/> Climb with 50 ft/min @ ISA+0 </td><td> ft </td><td>-</td><td>38945.9</td><td>-</td><td>-</td><td>-</td><td> </td>
+</tr>
+<tr>
+<td> One-engine-out (OEI) net ceiling <br/> Climb with 100 ft/min @ ISA+0 </td><td> ft </td><td>> 15000</td><td>21589.8</td><td>43.93</td><td>1</td><td>0</td><td> </td>
+</tr>
+<tr>
+<td> (Initial) Cruise Mach number </td><td> - </td><td>0.78</td><td>0.78</td><td>0</td><td>1</td><td>0</td><td> </td>
+</tr>
+<tr>
+<td> 2nd (T/O) Segment Climb Grad. </td><td> % </td><td>> 2.4</td><td>2.40917</td><td>0.38</td><td>1</td><td>0</td><td> </td>
+</tr>
+<tr>
+<td> Final (T/O) Segment Climb Grad. </td><td> % </td><td>> 1.2</td><td>2.40917</td><td>100.76</td><td>1</td><td>0</td><td> </td>
+</tr>
+<tr>
+<td> Approach Gradient (OEI) </td><td> % </td><td>2.1</td><td> - </td><td> - </td><td>1</td><td>0</td><td> </td>
+</tr>
+<tr>
+<td> Approach Gradient (AEO) </td><td> % </td><td>3.2</td><td> - </td><td> - </td><td>1</td><td>0</td><td> </td>
+</tr>
+</tbody>
+<tfoot/>
+</table>
+</div>
+<!-- CeRAS Report TLARs -->
+<!-- ################################################################################################### -->
+<div id="wrapper">
+<h2>Top-Level Aircraft Requirements:</h2>
+<table class="ceras" border="1" rules="groups">
+<colgroup>
+<col/>
+<col width="20%"/>
+<col width="20%"/>
+</colgroup>
+<thead align="left">
+<tr>
+<th>Parameter</th> <th>Unit</th> <th align="right">Req. Value</th>
+</tr>
+</thead>
+<tbody>
+<tr>
+<td>Design range</td><td> NM </td><td align="right">2500</td>
+</tr>
+<tr>
+<td>Design payload <br/> <font size="1">[200 lb (=90.72 kg) per PAX]</font></td><td> kg </td><td align="right">17000</td>
+</tr>
+<tr>
+<td>Maximum payload</td><td> kg </td><td align="right">20000</td>
+</tr>
+<tr>
+<td>(Initial) cruise Mach number</td><td> - </td><td align="right">0.78</td>
+</tr>
+<tr>
+<td>Max. operating Mach number (M<sub>MO</sub>)</td><td> kg </td><td align="right">0.82</td>
+</tr>
+<tr>
+<td>Max. operating speed (V<sub>MO</sub>)</td><td> kg </td><td align="right">350</td>
+</tr>
+<tr>
+<td> Initial Cruise Altitude (ICA) <br/> <font size="1">after T/O @ MTOM, ISA+0</font> </td><td> ft </td><td align="right">33000</td>
+</tr>
+<tr>
+<td> Time-to-climb (TTC) <br/> <font size="1">after T/O @ MTOM, ISA+0 (from 1500 ft to ICA)</font> </td><td> min </td><td align="right">< 35</td>
+</tr>
+<tr>
+<td> One-engine-out (OEI) net ceiling <br/> <font size="1">Climb with 100 ft/min @ ISA+0</font> </td><td> ft </td><td align="right">> 15000</td>
+</tr>
+<tr>
+<td> Max. operating (cruise) altitude <br/> <font size="1">Climb with 100 ft/min @ ISA+0</font> </td><td> ft </td><td align="right">> 38500</td>
+</tr>
+<tr>
+<td> Balanced Field Length (BFL) <br/> <font size="1">@ SL, MTOM, ISA+0</font> </td><td> m </td><td align="right">< 2122</td>
+</tr>
+<tr>
+<td> Landing distance (LDN) <br/> <font size="1">@ MLM, SL, ISA+0</font> </td><td> m </td><td align="right">< 2387</td>
+</tr>
+<tr>
+<td> Approach speed (v_app) </td><td> KCAS </td><td align="right">< 138</td>
+</tr>
+<tr>
+<td>Wing span limit</td><td> m </td><td align="right">≤ 36</td>
+</tr>
+<tr>
+<td>ACN (flex B)</td><td> - </td><td align="right">< 42</td>
+</tr>
+</tbody>
+<tfoot/>
+</table>
+</div>
+<!-- ################################################################################################### -->
+<!-- CeRAS Report KeyAircraftCharacteristics-->
+<!-- ################################################################################################### -->
+<div id="wrapper">
+<h2>Key Aircraft Characteristics:</h2>
+<table class="ceras" border="1" rules="groups">
+<colgroup>
+<col/>
+<col width="12%"/>
+<col width="12%"/>
+<col width="20%"/>
+</colgroup>
+<thead align="left">
+<tr>
+<th>Parameter</th> <th>Symbol</th> <th>Unit</th> <th align="right">Value</th>
+</tr>
+</thead>
+<tbody>
+<tr>
+<td>Design range</td><td><i>R</i></td><td>NM</td><td align="right">2500</td>
+</tr>
+<tr>
+<td>Design passenger capacity</td><td></td><td>PAX</td><td align="right">150</td>
+</tr>
+<tr>
+<td>Cruise Mach number</td><td><i>Ma<sub>Cr</sub></i></td><td>-</td><td align="right">0.78</td>
+</tr>
+<tr>
+</tr>
+<tr>
+</tr>
+<tr>
+<td>Wing loading</td><td><i>W/S</i></td><td>kg/m<sup>2</sup></td><td align="right">625.8</td>
+</tr>
+<tr>
+<td>Thrust-to-weight ratio</td><td><i>T/W</i></td><td>-</td><td align="right">0.332</td>
+</tr>
+<tr>
+</tr>
+<tr>
+</tr>
+<tr>
+<td>Maximum take-off mass</td><td><i>MTOM</i></td><td>t</td><td align="right">78.6</td>
+</tr>
+<tr>
+<td>Maximum landing mass</td><td><i>MLM</i></td><td>t</td><td align="right">66.3</td>
+</tr>
+<tr>
+<td>Operating mass empty</td><td><i>OME</i></td><td>t</td><td align="right">42.2</td>
+</tr>
+<tr>
+<td>Manufacturer's mass empty</td><td><i>MME</i></td><td>t</td><td align="right">38.8</td>
+</tr>
+<tr>
+<td>Maximum zero fuel mass</td><td><i>MZFM</i></td><td>t</td><td align="right">62.2</td>
+</tr>
+<tr>
+<td>Maximum fuel mass</td><td><i>MFM</i></td><td>t</td><td align="right">32.2</td>
+</tr>
+<tr>
+</tr>
+<tr>
+</tr>
+<tr>
+<td>Wing area</td><td><i>S<sub>ref</sub></i></td><td>m<sup>2</sup></td><td align="right">125.624</td>
+</tr>
+<tr>
+<td>Wing span</td><td><i>b</i></td><td>m</td><td align="right">34.546</td>
+</tr>
+<tr>
+<td>Mean aerodynamic chord</td><td><i>MAC</i></td><td>m</td><td align="right">4.38782</td>
+</tr>
+<tr>
+</tr>
+<tr>
+</tr>
+<tr>
+<td>Engine type</td><td></td><td>-</td><td align="right">2 x V2527-A5</td>
+</tr>
+<tr>
+<td>Sea-level static thrust</td><td><i>SLST</i></td><td>lbf / kN</td><td align="right">28778 / 128.009</td>
+</tr>
+</tbody>
+</table>
+<br><br>
+Material technology standard: aluminium wing and fuselage.
+</div>
+<!-- ################################################################################################### -->
+<div id="wrapper">
+<table class="ceras2Col" border="1" rules="groups">
+<thead>
+<tr class="title">
+<td rowspan="2">Iteration #</td> <td colspan="2">MTOM</td> <td colspan="2">OME</td> <td colspan="2">xCG</td> <td colspan="2">missionFuel</td>
+</tr>
+<tr class="title">
+<td>abs</td><td>rel</td> <td>abs</td><td>rel</td> <td>abs</td><td>rel</td> <td>abs</td><td>rel</td>
+</tr>
+</thead>
+<tbody>
+<tr>
+<td colspan="3"><b>Start values from Aircraft XML...</b></td>
+</tr>
+<tr>
+<td>0</td><td>78619.9</td><td></td><td>42154.3</td><td></td><td>16.8894</td><td></td><td>19566.5</td><td></td>
+</tr>
+<tr>
+<td colspan="3"><b>... after Setup Steps:</b></td>
+</tr>
+<tr>
+<td>0</td><td>78619.9</td><td></td><td>42154.3</td><td></td><td>16.8894</td><td></td><td>19566.5</td><td></td>
+</tr>
+</tbody>
+<tfoot/>
+</table>
+</div>
+</div>
+<font size="2">All outputs of the program 'convergenceLoop' were created with version 2.0.0
+</body>
+</html>
\ No newline at end of file
diff --git a/UnicadoGUI/Backend/output_files/reportHTML/empennageSizing_report.html b/UnicadoGUI/Backend/output_files/reportHTML/empennageSizing_report.html
new file mode 100644
index 0000000000000000000000000000000000000000..31373b6a638c2b70c63a34e5491f48c5ba9a2734
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/reportHTML/empennageSizing_report.html
@@ -0,0 +1,125 @@
+<!DOCTYPE html PUBLIC "-//W3C//DTD XHTML 1.0 Transitional//EN"
+ "http://www.w3.org/TR/xhtml1/DTD/xhtml1-transitional.dtd">
+<html xmlns="http://www.w3.org/1999/xhtml">
+<head>
+<meta http-equiv="content-type" content="text/html; charset=ISO-8859-1"/>
+<title>empennageSizing CeRAS-CSR-02</title>
+<style type="text/css">
+body,td,a,p{font-family:Times,sans-serif;font-size:12pt}
+h1{font-family:Times,sans-serif;font-size:14pt}
+h2{font-family:Times,sans-serif;font-size:12pt}
+body{color:#333;margin:15px;background:#fff;}
+table,img{border:0;max-width:100%}
+td,th{padding:5px;margin:5px}
+.ceras{width:100%}
+.ceras2Col{width:200%}
+#wrapper{width:100%;margin-bottom:1em;float:left}
+#leftCol{width:47.5%;float:left;margin-bottom:2em;}
+#rightCol{width:47.5%;margin-left:52.5%;margin-bottom:2em;}
+</style>
+</head>
+<body>
+<h1>Report of empennageSizing: CeRAS-CSR-02</h1>
+<!-- Begin CeRAS Report -->
+<!-- ################################################################################################### -->
+<div id="wrapper">
+<h1>Report CeRAS-CSR-02</h1>
+<h2>wing (MainWing):</h2>
+<table>
+<tr>
+<td> x-offest </td><td>12.53</td><td>m</td>
+</tr>
+<tr>
+<td>z-offset</td><td>-1.27</td><td>m</td>
+</tr>
+</table>
+<h2>parameter tailplane (Stabiliser):</h2>
+<table>
+<tr>
+<td>x-offest </td><td>31.67</td><td>m</td>
+</tr>
+<tr>
+<td>z-offset</td><td>1.65</td><td>m</td>
+</tr>
+<tr>
+<td>reference area</td><td>32.8</td><td>m²</td>
+</tr>
+<tr>
+<td>volume coefficient</td><td>1.0236</td><td></td>
+</tr>
+<tr>
+<td>span width</td><td>12.85</td><td>m</td>
+</tr>
+<tr>
+<td>aspect ratio</td><td>5.04</td><td></td>
+</tr>
+<tr>
+<td>inner thickness</td><td>3.98</td><td>m</td>
+</tr>
+<tr>
+<td>outside thickness</td><td>1.12</td><td>m</td>
+</tr>
+<tr>
+<td>taper ratio</td><td>0.28</td><td></td>
+</tr>
+<tr>
+<td>leading edge sweep</td><td>32</td><td>deg</td>
+</tr>
+<tr>
+<td>torsion</td><td>0</td><td>deg</td>
+</tr>
+<tr>
+<td>V-position</td><td>0</td><td>deg</td>
+</tr>
+<tr>
+<td>airfoil (inner)</td><td>n0012.dat</td><td></td>
+</tr>
+<tr>
+<td>airfoil (outer)</td><td>n0012.dat</td><td></td>
+</tr>
+</table>
+<h2>parameter fin (Fin):</h2>
+<table>
+<tr>
+<td>x-offest </td><td>29.87</td><td>m</td>
+</tr>
+<tr>
+<td>z-offset</td><td>1.65</td><td>m</td>
+</tr>
+<tr>
+<td>reference area</td><td>25.42</td><td>m²</td>
+</tr>
+<tr>
+<td>volume coefficient</td><td>0.096</td><td></td>
+</tr>
+<tr>
+<td>span width</td><td>6.95</td><td>m</td>
+</tr>
+<tr>
+<td>aspect ratio</td><td>1.9</td><td></td>
+</tr>
+<tr>
+<td>inner thickness</td><td>5.78</td><td>m</td>
+</tr>
+<tr>
+<td>outside thickness</td><td>1.53</td><td>m</td>
+</tr>
+<tr>
+<td>taper ratio</td><td>0.26</td><td></td>
+</tr>
+<tr>
+<td>leading edge sweep</td><td>39</td><td>deg</td>
+</tr>
+<tr>
+<td>airfoil (inner)</td><td>n0012.dat</td><td></td>
+</tr>
+<tr>
+<td>airfoil (outer)</td><td>n0012.dat</td><td></td>
+</tr>
+
+
+</table>
+</div>
+<font size="2">All outputs of the program 'empennageSizing' were created with version 2.0.0
+</body>
+</html>
\ No newline at end of file
diff --git a/UnicadoGUI/Backend/output_files/reportHTML/engineSizing_report.html b/UnicadoGUI/Backend/output_files/reportHTML/engineSizing_report.html
new file mode 100644
index 0000000000000000000000000000000000000000..2289c3253dc1ad670118494c0efd33044589e5e8
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/reportHTML/engineSizing_report.html
@@ -0,0 +1,108 @@
+<!DOCTYPE html PUBLIC "-//W3C//DTD XHTML 1.0 Transitional//EN"
+ "http://www.w3.org/TR/xhtml1/DTD/xhtml1-transitional.dtd">
+<html xmlns="http://www.w3.org/1999/xhtml">
+<head>
+<meta http-equiv="content-type" content="text/html; charset=ISO-8859-1"/>
+<title>engineSizing CeRAS-CSR-02</title>
+<style type="text/css">
+body,td,a,p{font-family:Times,sans-serif;font-size:12pt}
+h1{font-family:Times,sans-serif;font-size:14pt}
+h2{font-family:Times,sans-serif;font-size:12pt}
+body{color:#333;margin:15px;background:#fff;}
+table,img{border:0;max-width:100%}
+td,th{padding:5px;margin:5px}
+.ceras{width:100%}
+.ceras2Col{width:200%}
+#wrapper{width:100%;margin-bottom:1em;float:left}
+#leftCol{width:47.5%;float:left;margin-bottom:2em;}
+#rightCol{width:47.5%;margin-left:52.5%;margin-bottom:2em;}
+</style>
+</head>
+<body>
+<h1>Report of engineSizing: CeRAS-CSR-02</h1>
+<!-- Begin CeRAS Report -->
+<!-- ################################################################################################### -->
+<div id="wrapper">
+<div id="leftCol">
+<table class="ceras" border="1" rules="groups">
+<colgroup>
+<col/>
+<col width="25%"/>
+<col width="25%"/>
+</colgroup>
+<thead align="left">
+<tr>
+<th>Parameter</th><th>Unit</th><th align="right">Value</th>
+</tr>
+</thead>
+<tbody>
+<tr>
+<td>Engine Type</td><td>-</td><td align="right">2 x V2527-A5</td>
+</tr>
+<tr>
+<td>SLST <br><font size="1">(Flat rated thrust @ SL/Ma0/ISA+0)</font></td><td>kN</td><td align="right">128.01</td>
+</tr>
+<tr>
+<td></td><td>lbf</td><td align="right">28778</td>
+</tr>
+<tr>
+<td>Equivalent Thrust <br><font size="1">(1.25⋅thrust@SL/Ma0.25/ISA+0)</font></td><td>kN</td><td align="right">126.5</td>
+</tr>
+<tr>
+<td></td><td>lbf</td><td align="right">28447</td>
+</tr>
+<tr>
+<td><b>Average cruise offtakes (per engine)</b></td><td></td><td></td>
+</tr>
+<tr>
+<td> - Bleed air</td><td>kg/s</td><td align="right">0.44</td>
+</tr>
+<tr>
+<td> - Shaft power</td><td>kW</td><td align="right">51.6</td>
+</tr>
+</tbody>
+</table>
+<table class="ceras" border="1" rules="groups">
+<colgroup>
+<col/>
+<col width="10%"/>
+<col width="25%"/>
+<col width="25%"/>
+<col width="25%"/>
+</colgroup>
+<thead align="left">
+<tr>
+<th>Parameter</th><th>Unit</th><th align="right">Max. T/O <br/> <font size="1">(SL/Ma0.0/ISA+0)</font></th><th align="right">Bucket Pt. <br> <font size="1">(FL350/Ma0.8/ISA+0)</font></th><th align="right">Bucket Pt. <br> with offtakes <br> <font size="1">(FL350/Ma0.8/ISA+0/<br>Avg. Cruise Offtakes)</font></th>
+</tr>
+</thead>
+<tbody>
+<tr>
+<td>Thrust</td><td>kN</td><td align="right">128</td><td align="right">29.1</td><td align="right">29.1</td>
+</tr>
+<tr>
+<td></td><td>lbf</td><td align="right">28778</td><td align="right">6539</td><td align="right">6539</td>
+</tr>
+<tr>
+<td>Fuel flow</td><td>kg/s</td><td align="right">1.308</td><td align="right">0.493</td><td align="right">0.51</td>
+</tr>
+<tr>
+<td>TSFC</td><td>(kg/s)/N</td><td align="right">10.22</td><td align="right">16.94</td><td align="right">17.53</td>
+</tr>
+<tr>
+<td></td><td>(lb/hr)/lbf</td><td align="right">0.361</td><td align="right">0.598</td><td align="right">0.619</td>
+</tr>
+<tr>
+<td>N1</td><td>%</td><td align="right">97.8</td><td align="right">95</td><td align="right">95</td>
+</tr>
+</tbody>
+</table>
+</div>
+</div>
+<!-- ################################################################################################### -->
+<br>
+<hr>
+<br>
+</div>
+<font size="2">All outputs of the program 'engineSizing' were created with version 2.0.0
+</body>
+</html>
\ No newline at end of file
diff --git a/UnicadoGUI/Backend/output_files/reportHTML/fuselageDesign_report.html b/UnicadoGUI/Backend/output_files/reportHTML/fuselageDesign_report.html
new file mode 100644
index 0000000000000000000000000000000000000000..ff696d1674b507d1b7fc2907f718b74df80e4547
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/reportHTML/fuselageDesign_report.html
@@ -0,0 +1,353 @@
+<!DOCTYPE html PUBLIC "-//W3C//DTD XHTML 1.0 Transitional//EN"
+ "http://www.w3.org/TR/xhtml1/DTD/xhtml1-transitional.dtd">
+<html xmlns="http://www.w3.org/1999/xhtml">
+<head>
+<meta http-equiv="content-type" content="text/html; charset=ISO-8859-1"/>
+<title>fuselageDesign CeRAS-CSR-02</title>
+<style type="text/css">
+body,td,a,p{font-family:Times,sans-serif;font-size:12pt}
+h1{font-family:Times,sans-serif;font-size:14pt}
+h2{font-family:Times,sans-serif;font-size:12pt}
+body{color:#333;margin:15px;background:#fff;}
+table,img{border:0;max-width:100%}
+td,th{padding:5px;margin:5px}
+.ceras{width:100%}
+.ceras2Col{width:200%}
+#wrapper{width:100%;margin-bottom:1em;float:left}
+#leftCol{width:47.5%;float:left;margin-bottom:2em;}
+#rightCol{width:47.5%;margin-left:52.5%;margin-bottom:2em;}
+</style>
+</head>
+<body>
+<h1>Report of fuselageDesign: CeRAS-CSR-02</h1>
+<!-- Begin CeRAS Report -->
+<!-- ################################################################################################### -->
+<div id="wrapper">
+<div id="leftCol">
+<table class="ceras">
+<colgroup>
+<col/>
+<col width="30%"/>
+<col width="10%"/>
+<col width="10%"/>
+</colgroup>
+<thead align="left">
+<tr>
+<b><u>Fuselage dimensions (external)</u></b>
+<th>Parameter</th><th>Abbr./Symbol</th><th>Unit</th><th align="right">Value</th>
+</tr>
+</thead>
+<tbody>
+<tr>
+<td>Fuselage length (org)</td><td>l<sub>fuselage</sub></td><td>m</td><td align="right">37.53</td>
+</tr>
+<tr>
+<td>Fuselage length (calc)</td><td>l<sub>fuselage,calc</sub></td><td>m</td><td align="right">37.53</td>
+</tr>
+<tr>
+<td> Nose</td><td>l<sub>Nose</sub></td><td>m</td><td align="right">5.22</td>
+</tr>
+<tr>
+<td>  Cockpit</td><td>l<sub>cockpit</sub></td><td>m</td><td align="right">3.75</td>
+</tr>
+<tr>
+<td> Mid Section</td><td>l<sub>mid</sub></td><td>m</td><td align="right">16.76</td>
+</tr>
+<tr>
+<td>  Cabin</td><td>l<sub>cabin</sub></td><td>m</td><td align="right">26.86</td>
+</tr>
+<tr>
+<td> Tailcone length</td><td>l<sub>tail</sub></td><td>m</td><td align="right">15.55</td>
+</tr>
+<tr>
+<td>  aft pressure bulk</td><td>l<sub>tail, aft pressure bulk</sub></td><td>m</td><td align="right">6.919</td>
+</tr>
+<tr>
+<td>Width</td><td>w</td><td>m</td><td align="right">3.97</td>
+</tr>
+<tr>
+<td>Height</td><td>h</td><td>m</td><td align="right">4.14</td>
+</tr>
+<tr>
+<td>Cabin cross sectional area (total)</td><td>S</td><td>m<sup>2</sup></td><td align="right">12.9</td>
+</tr>
+</tbody>
+</table>
+<br>
+<br>
+<table class="ceras">
+<colgroup>
+<col/>
+<col width="30%"/>
+<col width="10%"/>
+<col width="10%"/>
+</colgroup>
+<thead align="left">
+<tr>
+<b><u>Fuselage dimensions (internal)</u></b>
+<th>Parameter</th><th>Abbr./Symbol</th><th>Unit</th><th align="right">Value</th>
+</tr>
+</thead>
+<tbody>
+<tr>
+<td>Length</td><td>l</td><td>m</td><td align="right">26.86</td>
+</tr>
+<tr>
+<td>Width</td><td>w</td><td>m</td><td align="right">3.66</td>
+</tr>
+<tr>
+<td>Height</td><td>h</td><td>m</td><td align="right">3.82</td>
+</tr>
+<tr>
+<td>Total Cross sectional area</td><td>S<sub>total</sub></td><td>m<sup>2</sup></td><td align="right">11</td>
+</tr>
+<tr>
+<td>Total Volume (pressurized)</td><td>V<sub>total</sub></td><td>m<sup>3</sup></td><td align="right">234.1</td>
+</tr>
+<tr>
+<td> Avionic Bay Volume</td><td>V<sub>avionics</sub></td><td>m<sup>3</sup></td><td align="right">12.02</td>
+</tr>
+<tr>
+<td> Cabin Volume</td><td>V<sub>avionics</sub></td><td>m<sup>3</sup></td><td align="right">186.1</td>
+</tr>
+<tr>
+<td> Cargo Volume</td><td>V<sub>avionics</sub></td><td>m<sup>3</sup></td><td align="right">35.92</td>
+</tr>
+</tbody>
+</table>
+<br>
+<br>
+<h2>Passenger accommodation:</h2>
+<table class="ceras">
+<colgroup>
+<col/>
+<col/>
+<col width="10%"/>
+<col width="10%"/>
+</colgroup>
+<thead align="left">
+<tr>
+<th>Parameter</th><th>Abbr./Symbol</th><th>Unit</th><th align="right">Value</th>
+</tr>
+</thead>
+<tbody>
+<tr>
+<td>Total number of PAX</td><td>PAX<sub>total</sub></td><td>-</td><td align="right">150</td>
+</tr>
+<tr>
+<td>Cabin attendants</td><td>CC</td><td>-</td><td align="right">4</td>
+</tr>
+<tr>
+<td>Flight crew members</td><td>FC</td><td>-</td><td align="right">2</td>
+</tr>
+<tr>
+<td class="line" colspan="5"></td>
+</tr>
+<tr>
+<td><i>Passenger Deck 1</i></td>
+</tr>
+<tr>
+<td> Cabin length</td><td>l<sub>cabin</sub></td><td>m</td><td align="right">26.86</td>
+</tr>
+<tr>
+<td>  business class</td><td>l<sub>cabin,business</sub></td><td>m</td><td align="right">4.466</td>
+</tr>
+<tr>
+<td>  economy class</td><td>l<sub>cabin,economy</sub></td><td>m</td><td align="right">22.39</td>
+</tr>
+<tr>
+<td> Max. cabin width<br><font size="1"> (armrest level)<br></td><td>w<sub>cabin</sub></td><td>m</td><td align="right">3.63</td>
+</tr>
+<tr>
+<td> Cabin height</td><td>h<sub>cabin</sub></td><td>m</td><td align="right">2.13</td>
+</tr>
+<tr>
+<td> Passenger cabin cross sectional area (water)</td><td>S<sub>cabin</sub></td><td>m<sup>2</sup></td><td align="right">6.93</td>
+</tr>
+<tr>
+<td> Passenger cabin volume (water)</td><td>V<sub>cabin</sub></td><td>m<sup>3</sup></td><td align="right">186.1</td>
+</tr>
+<tr>
+<td> Lavatories</td><td></td><td>-</td><td align="right">3</td>
+</tr>
+<tr>
+<td> Galleys</td><td></td><td>-</td><td align="right">2</td>
+</tr>
+<tr>
+<td>  business</td><td>small<br><font size="2">(20 PAX)</td><td>medium<br><font size="2">(40 PAX)</td><td align="right">large<br><font size="2">(80 PAX)</td>
+</tr>
+<tr>
+<td></td>
+<td>1</td><td>0</td><td align="right">0</td>
+</tr>
+<tr>
+<td>  economy</td><td>small<br><font size="2">(36 PAX)</td><td>medium<br><font size="2">(72 PAX)</td><td align="right">large<br><font size="2">(144 PAX)</td>
+</tr>
+<tr>
+<td></td>
+<td>0</td><td>0</td><td align="right">1</td>
+</tr>
+<tr>
+<td></td><td class="line" colspan="5"></td>
+</tr>
+<tr>
+<td colspan="4"><b>Seating Configuration</b></td>
+</tr>
+<tr>
+<td></td><td></td><td>business</td><td>economy</td>
+</tr>
+<tr>
+<td></td><td class="line" colspan="5"></td>
+</tr>
+<tr>
+<td> Number of seats</td><td>-</td><td>12</td><td>138</td>
+</tr>
+<tr>
+<td> Seating</td><td>-</td><td>2 - 2</td><td>3 - 3</td>
+</tr>
+<tr>
+<td> Seat width</td><td>m</td><td>0.7239</td><td>0.4995</td>
+</tr>
+<tr>
+<td> Seat depth</td><td>m</td><td>0.84</td><td>0.75</td>
+</tr>
+<tr>
+<td> Seat pitch</td><td>m</td><td>0.915</td><td>0.8128</td>
+</tr>
+<tr>
+<td> Seat mass</td><td>kg</td><td>t.b.d.</td><td>t.b.d.</td>
+</tr>
+<tr>
+<td class="line" colspan="5"></td>
+</tr>
+<tr>
+<td colspan="4"><b>Exits</b></td>
+</tr>
+<tr>
+<td> Exit Type A </td><td>#</td><td>-</td><td align="right">0</td>
+<tr>
+<td> Exit Type B </td><td>#</td><td>-</td><td align="right">0</td>
+</tr>
+<tr>
+<td> Exit Type C </td><td>#</td><td>-</td><td align="right">0</td>
+</tr>
+<tr>
+<td> Exit Type I </td><td>#</td><td>-</td><td align="right">2</td>
+</tr>
+<tr>
+<td> Exit Type II </td><td>#</td><td>-</td><td align="right">0</td>
+</tr>
+<tr>
+<td> Overwing Exit Type III </td><td>#</td><td>-</td><td align="right">2</td>
+</tr>
+<tr>
+<td> Overwing Exit Type IV</td><td>#</td><td>-</td><td align="right">0</td>
+</tr>
+<tr>
+<td colspan="4"> business Class</td></tr>
+<tr>
+<td>  Position 1</td><td>x<sub>ref,1</sub></td><td>m</td><td align="right">4.816</td>
+</tr>
+<tr>
+<td colspan="4"> economy Class</td></tr>
+<tr>
+<td>  Position 1</td><td>x<sub>ref,1</sub></td><td>m</td><td align="right">28.21</td>
+</tr>
+<tr>
+<td>  Position 2</td><td>x<sub>ref,2</sub></td><td>m</td><td align="right">13.35</td>
+</tr>
+<tr>
+<td>  Position 3</td><td>x<sub>ref,3</sub></td><td>m</td><td align="right">14.61</td>
+</tr>
+</tr>
+<tr>
+<td></td><td class="line" colspan="5"></td>
+</tr>
+<tr>
+<td colspan="4"><b>Reference Points (Length Direction)</b></td>
+</tr>
+<tr>
+<td>business</td><td>x<sub>ref</sub></td><td>m</td><td align="right">5.983</td>
+</tr>
+<tr>
+<td>economy</td><td>x<sub>ref</sub></td><td>m</td><td align="right">19.41</td>
+</tr>
+</tbody>
+</table>
+<br>
+<br>
+<h2>Cargo accommodation:</h2>
+<table class="ceras">
+<colgroup>
+<col/>
+<col width="30%"/>
+<col width="10%"/>
+<col width="10%"/>
+</colgroup>
+<thead align="left">
+<tr>
+<th>Parameter</th><th>Abbr./Symbol</th><th>Unit</th><th align="right">Value</th>
+</tr>
+</thead>
+<tbody>
+<tr>
+<td><i>Cargo Deck 1</i></td>
+</tr>
+<tr>
+<td> Cargo length<br><font size="1"> (with wingbox)<br></td><td>l<sub>cargo</sub></td><td>m</td><td align="right">17.2</td>
+</tr>
+<tr>
+<td>  forward compartment</td><td>l<sub>cargo,forward</sub></td><td>m</td><td align="right">4.84</td>
+</tr>
+<tr>
+<td>  aft compartment</td><td>l<sub>cargo,aft</sub></td><td>m</td><td align="right">6.37</td>
+</tr>
+<tr>
+<td> Max. cargo width</td><td>w<sub>cargo</sub></td><td>m</td><td align="right">3.28</td>
+</tr>
+<tr>
+<td> Cargo height</td><td>h<sub>cargo</sub></td><td>m</td><td align="right">1.14</td>
+</tr>
+<tr>
+<td> Cargo cross sectional area (water)</td><td>S<sub>cargo</sub></td><td>m<sup>2</sup></td><td align="right">3.2</td>
+</tr>
+<tr>
+<td> Cargo volume (water)</td><td>V<sub>cargo</sub></td><td>m<sup>3</sup></td><td align="right">35.92</td>
+</tr>
+<tr>
+<td>  forward compartment</td><td>V<sub>cargo,forward</sub></td><td>m<sup>3</sup></td><td align="right">15.51</td>
+</tr>
+<tr>
+<td>  aft compartment</td><td>V<sub>cargo,aft</sub></td><td>m<sup>3</sup></td><td align="right">20.41</td>
+</tr>
+</tbody>
+</table>
+<br>
+<br>
+</div>
+</div>
+<!-- ################################################################################################### -->
+<hr>
+<div id="wrapper">
+<div id="leftCol">
+<p></p>
+<h3>Cabin Layouts</h3>
+<img src="..\plots\fuselageDesign_CrossSectionLayout_0.svg">
+<img src="..\plots\fuselageDesign_CrossSectionLayout_1.svg">
+<img src="..\plots\fuselageDesign_CrossSectionLayout_2.svg">
+<img src="..\plots\fuselageDesign_CrossSectionLayout_3.svg">
+<img src="..\plots\fuselageDesign_CrossSectionLayout_4.svg">
+<p></p>
+<h3>Cross Section Layouts</h3>
+<img src="..\plots\fuselageDesign_CompartmentLayout_Deck1of1.svg">
+<p></p>
+<img src="..\plots\fuselageDesign_CabinLayout_Deck1of1.svg">
+<p></p>
+<img src="..\plots\fuselageDesign_CabinLayout_Deck_sideview.svg">
+<p></p>
+</div>
+</div>
+</div>
+<font size="2">All outputs of the program 'fuselageDesign' were created with version 2.0.0
+</body>
+</html>
\ No newline at end of file
diff --git a/UnicadoGUI/Backend/output_files/reportHTML/landingGearDesign_report.html b/UnicadoGUI/Backend/output_files/reportHTML/landingGearDesign_report.html
new file mode 100644
index 0000000000000000000000000000000000000000..993e44d681674f147face0cf42652b4129a2f604
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/reportHTML/landingGearDesign_report.html
@@ -0,0 +1,44 @@
+<!DOCTYPE html PUBLIC "-//W3C//DTD XHTML 1.0 Transitional//EN"
+ "http://www.w3.org/TR/xhtml1/DTD/xhtml1-transitional.dtd">
+<html xmlns="http://www.w3.org/1999/xhtml">
+<head>
+<meta http-equiv="content-type" content="text/html; charset=ISO-8859-1"/>
+<title>landingGearDesign CeRAS-CSR-02</title>
+<style type="text/css">
+body,td,a,p{font-family:Times,sans-serif;font-size:12pt}
+h1{font-family:Times,sans-serif;font-size:14pt}
+h2{font-family:Times,sans-serif;font-size:12pt}
+body{color:#333;margin:15px;background:#fff;}
+table,img{border:0;max-width:100%}
+td,th{padding:5px;margin:5px}
+.ceras{width:100%}
+.ceras2Col{width:200%}
+#wrapper{width:100%;margin-bottom:1em;float:left}
+#leftCol{width:47.5%;float:left;margin-bottom:2em;}
+#rightCol{width:47.5%;margin-left:52.5%;margin-bottom:2em;}
+</style>
+</head>
+<body>
+<h1>Report of landingGearDesign: CeRAS-CSR-02</h1>
+<!-- Begin CeRAS Report -->
+<!-- ################################################################################################### -->
+<div id="wrapper">
+<h2>Landing gear positions</h2>
+<table>
+<tr>
+<td>Wheel base (NLG to MLG)</td><td>14.32</td><td>m</td>
+</tr>
+<tr>
+<td>Wheel track (MLG)</td><td>8.50</td><td>m</td>
+</tr>
+<tr>
+<td>Reference point MLG</td><td>17.84</td><td>m</td>
+</tr>
+<tr>
+<td>Reference point NLG</td><td>3.48</td><td>m</td>
+</tr>
+</table>
+</div>
+<font size="2">All outputs of the program 'landingGearDesign' were created with version 2.0.0
+</body>
+</html>
\ No newline at end of file
diff --git a/UnicadoGUI/Backend/output_files/reportHTML/propulsionIntegration_report.html b/UnicadoGUI/Backend/output_files/reportHTML/propulsionIntegration_report.html
new file mode 100644
index 0000000000000000000000000000000000000000..804f702ce77a7729eafe0879a83266e360f60dd9
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/reportHTML/propulsionIntegration_report.html
@@ -0,0 +1,51 @@
+<!DOCTYPE html PUBLIC "-//W3C//DTD XHTML 1.0 Transitional//EN"
+ "http://www.w3.org/TR/xhtml1/DTD/xhtml1-transitional.dtd">
+<html xmlns="http://www.w3.org/1999/xhtml">
+<head>
+<meta http-equiv="content-type" content="text/html; charset=ISO-8859-1"/>
+<title>propulsionIntegration </title>
+<style type="text/css">
+body,td,a,p{font-family:Times,sans-serif;font-size:12pt}
+h1{font-family:Times,sans-serif;font-size:14pt}
+h2{font-family:Times,sans-serif;font-size:12pt}
+body{color:#333;margin:15px;background:#fff;}
+table,img{border:0;max-width:100%}
+td,th{padding:5px;margin:5px}
+.ceras{width:100%}
+.ceras2Col{width:200%}
+#wrapper{width:100%;margin-bottom:1em;float:left}
+#leftCol{width:47.5%;float:left;margin-bottom:2em;}
+#rightCol{width:47.5%;margin-left:52.5%;margin-bottom:2em;}
+</style>
+</head>
+<body>
+<h1>Report of propulsionIntegration: </h1>
+<!-- Begin CeRAS Report -->
+<!-- ################################################################################################### -->
+<div id="wrapper">
+<h2>Positions of the nacelles</h2>
+<div id="leftCol">
+<table class="ceras">
+<colgroup>
+<col/>
+<col width="20%"/>
+<col width="10%"/>
+<col width="10%"/>
+</colgroup>
+<tr>
+<td>TW #</td><td>X<sub>ref</sub></td><td>Y<sub>ref</sub></td><td>Z<sub>ref</sub></td>
+</tr>
+<tr>
+<td>1</td><td>13.3224</td><td>5.48094</td><td>-3.06841</td>
+</tr>
+<tr>
+<td>2</td><td>13.3224</td><td>-5.48094</td><td>-3.06841</td>
+</tr>
+</table>
+</div>
+<div id="rightCol">
+</div>
+</div>
+<font size="2">All outputs of the program 'propulsionIntegration' were created with version 2.0.0
+</body>
+</html>
\ No newline at end of file
diff --git a/UnicadoGUI/Backend/output_files/reportHTML/wingDesign_report.html b/UnicadoGUI/Backend/output_files/reportHTML/wingDesign_report.html
new file mode 100644
index 0000000000000000000000000000000000000000..8ef86dca8cd3181f865982ea4d0ffee47206ece2
--- /dev/null
+++ b/UnicadoGUI/Backend/output_files/reportHTML/wingDesign_report.html
@@ -0,0 +1,158 @@
+<!DOCTYPE html PUBLIC "-//W3C//DTD XHTML 1.0 Transitional//EN"
+ "http://www.w3.org/TR/xhtml1/DTD/xhtml1-transitional.dtd">
+<html xmlns="http://www.w3.org/1999/xhtml">
+<head>
+<meta http-equiv="content-type" content="text/html; charset=ISO-8859-1"/>
+<title>wingDesign CeRAS-CSR-02</title>
+<style type="text/css">
+body,td,a,p{font-family:Times,sans-serif;font-size:12pt}
+h1{font-family:Times,sans-serif;font-size:14pt}
+h2{font-family:Times,sans-serif;font-size:12pt}
+body{color:#333;margin:15px;background:#fff;}
+table,img{border:0;max-width:100%}
+td,th{padding:5px;margin:5px}
+.ceras{width:100%}
+.ceras2Col{width:200%}
+#wrapper{width:100%;margin-bottom:1em;float:left}
+#leftCol{width:47.5%;float:left;margin-bottom:2em;}
+#rightCol{width:47.5%;margin-left:52.5%;margin-bottom:2em;}
+</style>
+</head>
+<body>
+<h1>Report of wingDesign: CeRAS-CSR-02</h1>
+<!-- Begin CeRAS Report -->
+<!-- ################################################################################################### -->
+<div id="wrapper">
+<h2>Wing Planform Parameters:</h2>
+<div id="leftCol">
+<table class="ceras">
+<colgroup>
+<col/>
+<col width="30%"/>
+<col width="10%"/>
+<col width="10%"/>
+</colgroup>
+<hr>
+<thead align="left">
+<tr>
+<th>Parameter</th><th>Symbol</th><th>Unit</th><th align="right">Value</th>
+</tr>
+</thead>
+<tr>
+<td>Wing area</td><td>S<sub>ref</sub></td><td>m<sup>2</sup></td><td align="right">125.62</td>
+</tr>
+<tr>
+<td>Mean aerodynamic chord</td><td>MAC</td><td>m</td><td align="right">4.388</td>
+</tr>
+<tr>
+<td>Wing span</td><td>b</td><td>m</td><td align="right">34.546</td>
+</tr>
+<tr>
+<td>Aspect ratio</td><td>Λ</td><td>-</td><td align="right">9.50</td>
+</tr>
+<tr>
+<td>Taper ratio</td><td>λ</td><td>-</td><td align="right">0.17</td>
+</tr>
+</table>
+<br>
+<h2>Wing Section Parameters at η = y/c:</h2>
+<table class="ceras">
+<colgroup>
+<col/>
+<col width="20%"/>
+<col width="10%"/>
+<col width="10%"/>
+<col/>
+</colgroup>
+<hr>
+<thead align="left">
+<tr>
+<th>Parameter</th><th>Symbol</th><th>Unit</th><th align="center" colspan="3">Values</th>
+</tr>
+</thead>
+<thead align="left">
+<tr>
+<th></th><th>η</th><th>-</th><th align="right">0.000</th><th align="right">0.300</th><th align="right">1.000</th>
+</tr>
+</thead>
+<thead align="left">
+<tr>
+<th></th><th>y</th><th>m</th><th align="right">0.000</th><th align="right">5.182</th><th align="right">17.273</th>
+</tr>
+</thead>
+<tbody>
+<tr>
+<td>Chord length</td><td>c</td><td>m</td><td align="right">7.060</td><td align="right">4.420</td><td align="right">1.050</td>
+</tr>
+<tr>
+<td>QC sweep angle</td><td>φ<sub>25</sub></td><td>°</td><td align="right">20.91</td><td align="right">23.74</td>
+</tr>
+<tr>
+<td>LE sweep angle</td><td>φ<sub>LE</sub></td><td>°</td><td align="right">27.00</td><td align="right">27.00</td>
+</tr>
+<tr>
+<td>TE sweep angle</td><td>φ<sub>TE</sub></td><td>°</td><td align="right">0.00</td><td align="right">13.00</td>
+</tr>
+<tr>
+<td>Dihedral</td><td>ν</td><td>°</td><td align="right">2.09</td><td align="right">2.37</td>
+</tr>
+<tr>
+<td>Twist angle</td><td>ε</td><td>°</td><td align="right">0.00</td><td align="right">0.00</td><td align="right">0.00</td>
+</tr>
+<tr>
+<td>Thickness ratio</td><td>t/c</td><td>%</td><td align="right">15.00</td><td align="right">11.99</td><td align="right">10.99</td>
+</tr>
+<tr>
+<td>Airfoils</td><td></td><td></td><td align="right">A1</td><td align="right">A2</td><td align="right">A3</td>
+</tr>
+<tr>
+<td class="line" colspan="6"><b>Relative chord spar positions</b></td>
+</tr>
+<tr>
+<td>Front spar</td><td>x/c</td><td>%</td><td align="right">11.00</td><td align="right">16.00</td><td align="right">27.00</td>
+</tr>
+<tr>
+<td>Rear spar</td><td>x/c</td><td>%</td><td align="right">55.00</td><td align="right">65.00</td><td align="right">55.00</td>
+</tr>
+</tbody>
+</table>
+<hr>
+<font size="1">Sweep angles and dihedral at spanwise stations η refer to the respective inner adjacent segment.</font>
+<br><br>
+<h2>Fuel Tank Capacities:</h2>
+1 Centre tank with 8215 kg.<br>
+2 Wing tanks with 11982 kg each.<br>
+<br>
+Total fuel mass: 32179 kg.
+</div>
+<div id="rightCol">
+<img class="ceras" src="..\plots\wingDesign_plot.svg"/>
+</div>
+<div id="rightCol">
+<img class="ceras" src="..\plots\wingDesign_airfoil_plot.svg"/>
+</div>
+</div>
+<div id="wrapper">
+<div id="leftCol">
+<h2>Leading Edge Arrangement:</h2>
+<ul>
+<li>1 outboard slat from 0.11 (at η = 0.12) to 0.27 (at η = 0.95) local chord.
+</ul>
+</div>
+<div id="rightCol">
+<h2>Trailing Edge Arrangement:</h2>
+<li>1 inboard Fowler flap from 0.20 (at η = 0.12) to 0.30 (at η = 0.29) local chord.
+<li>1 inboard (ground)spoiler from 0.12 (at η = 0.21) to 0.15 (at η = 0.29) local chord.
+<li>1 outboard aileron from 0.30 (at η = 0.80) to 0.30 (at η = 0.98) local chord.
+<li>1 outboard Fowler flap from 0.30 (at η = 0.31) to 0.30 (at η = 0.78) local chord.
+<li>4 outboard (air)spoiler from 0.15 (at η = 0.31) to 0.15 (at η = 0.76) local chord.
+</ul>
+</div>
+</div>
+<!-- ################################################################################################### -->
+<hr>
+<hr>
+</div>
+<font size="2">All outputs of the program 'wingDesign' were created with version 2.0.0
+</body>
+</html>
\ No newline at end of file