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UnicadoGuiBackend

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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
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