add some example outputfiles

UnicadoGUI/Backend/output_files/logFiles/calculatePolar.log

+*******************************************************************************
+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

UnicadoGUI/Backend/output_files/logFiles/createMissionXML.log

+*******************************************************************************
+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

UnicadoGUI/Backend/output_files/logFiles/empennageSizing.log

+*******************************************************************************
+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

UnicadoGUI/Backend/output_files/logFiles/engineSizing.log

+*******************************************************************************
+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

UnicadoGUI/Backend/output_files/logFiles/fuselageDesign.log

+*******************************************************************************
+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

UnicadoGUI/Backend/output_files/logFiles/initialSizing.log

+*******************************************************************************
+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

UnicadoGUI/Backend/output_files/logFiles/landingGearDesign.log

+*******************************************************************************
+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

UnicadoGUI/Backend/output_files/logFiles/propulsionIntegration.log

+*******************************************************************************
+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

UnicadoGUI/Backend/output_files/logFiles/wingDesign.log

+*******************************************************************************
+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

UnicadoGUI/Backend/output_files/reportHTML/convergenceLoop_report.html

+<!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>&lt; 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>&lt; 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>&lt; 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>&lt; 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>&gt; 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>&gt; 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>&gt; 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>&gt; 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">&lt; 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">&gt; 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">&gt; 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">&lt; 2122</td>
+</tr>
+<tr>
+<td>  Landing distance (LDN) <br/> <font size="1">@ MLM, SL, ISA+0</font>  </td><td>  m  </td><td align="right">&lt; 2387</td>
+</tr>
+<tr>
+<td>  Approach speed (v_app)  </td><td>  KCAS  </td><td align="right">&lt; 138</td>
+</tr>
+<tr>
+<td>Wing span limit</td><td>  m  </td><td align="right">&le; 36</td>
+</tr>
+<tr>
+<td>ACN (flex B)</td><td>  -  </td><td align="right">&lt; 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

UnicadoGUI/Backend/output_files/reportHTML/empennageSizing_report.html

+<!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>m&sup2;</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>m&sup2;</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

UnicadoGUI/Backend/output_files/reportHTML/engineSizing_report.html

+<!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&sdot;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

UnicadoGUI/Backend/output_files/reportHTML/fuselageDesign_report.html

+<!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>&emsp;Nose</td><td>l<sub>Nose</sub></td><td>m</td><td align="right">5.22</td>
+</tr>
+<tr>
+<td>&emsp;&emsp;Cockpit</td><td>l<sub>cockpit</sub></td><td>m</td><td align="right">3.75</td>
+</tr>
+<tr>
+<td>&emsp;Mid Section</td><td>l<sub>mid</sub></td><td>m</td><td align="right">16.76</td>
+</tr>
+<tr>
+<td>&emsp;&emsp;Cabin</td><td>l<sub>cabin</sub></td><td>m</td><td align="right">26.86</td>
+</tr>
+<tr>
+<td>&emsp;Tailcone length</td><td>l<sub>tail</sub></td><td>m</td><td align="right">15.55</td>
+</tr>
+<tr>
+<td>&emsp;&emsp;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>&emsp;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>&emsp;Cabin Volume</td><td>V<sub>avionics</sub></td><td>m<sup>3</sup></td><td align="right">186.1</td>
+</tr>
+<tr>
+<td>&emsp;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>&emsp;Cabin length</td><td>l<sub>cabin</sub></td><td>m</td><td align="right">26.86</td>
+</tr>
+<tr>
+<td>&emsp;&emsp;business class</td><td>l<sub>cabin,business</sub></td><td>m</td><td align="right">4.466</td>
+</tr>
+<tr>
+<td>&emsp;&emsp;economy class</td><td>l<sub>cabin,economy</sub></td><td>m</td><td align="right">22.39</td>
+</tr>
+<tr>
+<td>&emsp;Max. cabin width<br><font size="1">&emsp;(armrest level)<br></td><td>w<sub>cabin</sub></td><td>m</td><td align="right">3.63</td>
+</tr>
+<tr>
+<td>&emsp;Cabin height</td><td>h<sub>cabin</sub></td><td>m</td><td align="right">2.13</td>
+</tr>
+<tr>
+<td>&emsp;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>&emsp;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>&emsp;Lavatories</td><td></td><td>-</td><td align="right">3</td>
+</tr>
+<tr>
+<td>&emsp;Galleys</td><td></td><td>-</td><td align="right">2</td>
+</tr>
+<tr>
+<td>&emsp;&emsp;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>&emsp;&emsp;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>&emsp;Number of seats</td><td>-</td><td>12</td><td>138</td>
+</tr>
+<tr>
+<td>&emsp;Seating</td><td>-</td><td>2 - 2</td><td>3 - 3</td>
+</tr>
+<tr>
+<td>&emsp;Seat width</td><td>m</td><td>0.7239</td><td>0.4995</td>
+</tr>
+<tr>
+<td>&emsp;Seat depth</td><td>m</td><td>0.84</td><td>0.75</td>
+</tr>
+<tr>
+<td>&emsp;Seat pitch</td><td>m</td><td>0.915</td><td>0.8128</td>
+</tr>
+<tr>
+<td>&emsp;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>&emsp;Exit Type A </td><td>#</td><td>-</td><td align="right">0</td>
+<tr>
+<td>&emsp;Exit Type B </td><td>#</td><td>-</td><td align="right">0</td>
+</tr>
+<tr>
+<td>&emsp;Exit Type C </td><td>#</td><td>-</td><td align="right">0</td>
+</tr>
+<tr>
+<td>&emsp;Exit Type I </td><td>#</td><td>-</td><td align="right">2</td>
+</tr>
+<tr>
+<td>&emsp;Exit Type II </td><td>#</td><td>-</td><td align="right">0</td>
+</tr>
+<tr>
+<td>&emsp;Overwing Exit Type III </td><td>#</td><td>-</td><td align="right">2</td>
+</tr>
+<tr>
+<td>&emsp;Overwing Exit Type IV</td><td>#</td><td>-</td><td align="right">0</td>
+</tr>
+<tr>
+<td colspan="4">&emsp;business Class</td></tr>
+<tr>
+<td>&emsp;&emsp;Position 1</td><td>x<sub>ref,1</sub></td><td>m</td><td align="right">4.816</td>
+</tr>
+<tr>
+<td colspan="4">&emsp;economy Class</td></tr>
+<tr>
+<td>&emsp;&emsp;Position 1</td><td>x<sub>ref,1</sub></td><td>m</td><td align="right">28.21</td>
+</tr>
+<tr>
+<td>&emsp;&emsp;Position 2</td><td>x<sub>ref,2</sub></td><td>m</td><td align="right">13.35</td>
+</tr>
+<tr>
+<td>&emsp;&emsp;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>&emsp;Cargo length<br><font size="1">&emsp;(with wingbox)<br></td><td>l<sub>cargo</sub></td><td>m</td><td align="right">17.2</td>
+</tr>
+<tr>
+<td>&emsp;&emsp;forward compartment</td><td>l<sub>cargo,forward</sub></td><td>m</td><td align="right">4.84</td>
+</tr>
+<tr>
+<td>&emsp;&emsp;aft compartment</td><td>l<sub>cargo,aft</sub></td><td>m</td><td align="right">6.37</td>
+</tr>
+<tr>
+<td>&emsp;Max. cargo width</td><td>w<sub>cargo</sub></td><td>m</td><td align="right">3.28</td>
+</tr>
+<tr>
+<td>&emsp;Cargo height</td><td>h<sub>cargo</sub></td><td>m</td><td align="right">1.14</td>
+</tr>
+<tr>
+<td>&emsp;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>&emsp;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>&emsp;&emsp;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>&emsp;&emsp;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

UnicadoGUI/Backend/output_files/reportHTML/landingGearDesign_report.html

+<!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

UnicadoGUI/Backend/output_files/reportHTML/propulsionIntegration_report.html

+<!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

UnicadoGUI/Backend/output_files/reportHTML/wingDesign_report.html

+<!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>&Lambda;</td><td>-</td><td align="right">9.50</td>
+</tr>
+<tr>
+<td>Taper ratio</td><td>&lambda;</td><td>-</td><td align="right">0.17</td>
+</tr>
+</table>
+<br>
+<h2>Wing Section Parameters at &eta; = 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>&eta;</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>&phi;<sub>25</sub></td><td>&deg;</td><td align="right">20.91</td><td align="right">23.74</td>
+</tr>
+<tr>
+<td>LE sweep angle</td><td>&phi;<sub>LE</sub></td><td>&deg;</td><td align="right">27.00</td><td align="right">27.00</td>
+</tr>
+<tr>
+<td>TE sweep angle</td><td>&phi;<sub>TE</sub></td><td>&deg;</td><td align="right">0.00</td><td align="right">13.00</td>
+</tr>
+<tr>
+<td>Dihedral</td><td>&nu;</td><td>&deg;</td><td align="right">2.09</td><td align="right">2.37</td>
+</tr>
+<tr>
+<td>Twist angle</td><td>&epsilon;</td><td>&deg;</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 &eta; 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 &eta; = 0.12) to 0.27 (at &eta; = 0.95) local chord.
+</ul>
+</div>
+<div id="rightCol">
+<h2>Trailing Edge Arrangement:</h2>
+<li>1 inboard Fowler flap from 0.20 (at &eta; = 0.12) to 0.30 (at &eta; = 0.29) local chord.
+<li>1 inboard (ground)spoiler from 0.12 (at &eta; = 0.21) to 0.15 (at &eta; = 0.29) local chord.
+<li>1 outboard aileron from 0.30 (at &eta; = 0.80) to 0.30 (at &eta; = 0.98) local chord.
+<li>1 outboard Fowler flap from 0.30 (at &eta; = 0.31) to 0.30 (at &eta; = 0.78) local chord.
+<li>4 outboard (air)spoiler from 0.15 (at &eta; = 0.31) to 0.15 (at &eta; = 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