Passed
gpkit.tests.from_paths.TestFiles.test_SP_aircraft_py_mosek (from gpkit.tests.from_paths.TestFiles-20171014234038)
Standard Output
Beginning signomial solve. Solving took 7 GP solves and 44.8 seconds. Warning: Constraint [W_{avg}_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0)*x_{CG}_Mission/CruiseSegment/CruiseP/Aircra... >= 0.225*W_{ht}_Mission/Aircraft/HorizontalTail*x_{CG_{ht}}_Mission/Aircraft/HorizontalTail/HorizontalT...] is not tight because the left hand side evaluated to 2427084.51985 force_pound * meter but the right hand side evaluated to 2397886.40106 force_pound * meter (Allowable error: 0.1%, Actual error: 1.2%) Warning: Constraint [0.0417*S_Mission/Aircraft/Wing/WingNoStruct**-1*\tan(\Lambda)_Mission/Aircraft/Wing/WingNoStruct*b_M... >= \Delta x_{AC_{wing}}_Mission/Aircraft/Wing [m]...] is not tight because the left hand side evaluated to 2.21510116727 meter but the right hand side evaluated to 1.9646923471 meter (Allowable error: 0.1%, Actual error: 11%) Warning: Constraint [F_{6}_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(3, 0) + F_{8}_Mission/Aircraft/En... >= F_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(3, 0) [N]...] is not tight because the left hand side evaluated to 17472.5869143 newton but the right hand side evaluated to 17443.2539197 newton (Allowable error: 0.1%, Actual error: 0.17%) Warning: Constraint [-C_{p_{fuel}_Mission/Aircraft/Engine/Combustor*T_{t_f}_Mission/Aircraft/Engine/Combustor*f_Mission/A... <= \eta_{B}_Mission/Aircraft/Engine/Combustor*f_Mission/Aircraft/Engine/EnginePerformance/CombustorPerf...] is not tight because the left hand side evaluated to 1242117.41123 joule / kilogram but the right hand side evaluated to 1.48135685075 megajoule / kilogram (Allowable error: 0.1%, Actual error: 9.5%) Warning: Constraint [-C_{p_{fuel}_Mission/Aircraft/Engine/Combustor*T_{t_f}_Mission/Aircraft/Engine/Combustor*f_Mission/A... <= \eta_{B}_Mission/Aircraft/Engine/Combustor*f_Mission/Aircraft/Engine/EnginePerformance/CombustorPerf...] is not tight because the left hand side evaluated to 642471.441536 joule / kilogram but the right hand side evaluated to 0.643955968848 megajoule / kilogram (Allowable error: 0.1%, Actual error: 0.1%) Warning: Constraint [W_{lg}_Mission/Aircraft/LandingGear*x_{CG_{lg}}_Mission/Aircraft/LandingGear [N*m]... >= W_{mg}_Mission/Aircraft/LandingGear*x_m_Mission/Aircraft/LandingGear + W_{ng}_Mission/Aircraft/Landi...] is not tight because the left hand side evaluated to 271789.864137 meter * newton but the right hand side evaluated to 263035.01714 meter * newton (Allowable error: 1.0%, Actual error: 3.3%) Warning: Constraint [x_m_Mission/Aircraft/LandingGear [m]... >= x_{wing}_Mission/Aircraft/Fuselage [m]...] is not tight because the left hand side evaluated to 18.5759874075 meter but the right hand side evaluated to 16.6120674332 meter (Allowable error: 0.1%, Actual error: 12%) Warning: Constraint [C_{L_{ht}}_Mission/ClimbSegment/ClimbP/AircraftP/HorizontalTailPerformance_(0, 0)*C_{L}_Mission/Clim... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/ClimbSegment/ClimbP/AircraftP_(0, 0)...] is not tight because the left hand side evaluated to 10.9551830146 but the right hand side evaluated to 4.85819888936 (Allowable error: 0.1%, Actual error: 56%) Warning: Constraint [C_{L_{ht}}_Mission/ClimbSegment/ClimbP/AircraftP/HorizontalTailPerformance_(1, 0)*C_{L}_Mission/Clim... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/ClimbSegment/ClimbP/AircraftP_(1, 0)...] is not tight because the left hand side evaluated to 10.0069441421 but the right hand side evaluated to 4.85820911316 (Allowable error: 0.1%, Actual error: 51%) Warning: Constraint [C_{L_{ht}}_Mission/ClimbSegment/ClimbP/AircraftP/HorizontalTailPerformance_(2, 0)*C_{L}_Mission/Clim... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/ClimbSegment/ClimbP/AircraftP_(2, 0)...] is not tight because the left hand side evaluated to 8.21525673431 but the right hand side evaluated to 4.85820918084 (Allowable error: 0.1%, Actual error: 41%) Warning: Constraint [0.25*\Delta x_{AC_{wing}}_Mission/Aircraft/Wing + x_{NP}_Mission/CruiseSegment/CruiseP/AircraftP.1_(... >= x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(0, 0) [m]...] is not tight because the left hand side evaluated to 18.6220169229 meter but the right hand side evaluated to 18.3758791082 meter (Allowable error: 0.1%, Actual error: 1.3%) Warning: Constraint [0.25*\Delta x_{AC_{wing}}_Mission/Aircraft/Wing + x_{NP}_Mission/CruiseSegment/CruiseP/AircraftP.1_(... >= x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0) [m]...] is not tight because the left hand side evaluated to 18.6220169229 meter but the right hand side evaluated to 18.4513396746 meter (Allowable error: 0.1%, Actual error: 0.92%) Warning: Constraint [SM_Mission/CruiseSegment/CruiseP/AircraftP.1_(0, 0) + mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{... <= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(0, 0)...] is not tight because the left hand side evaluated to 4.67772090418 but the right hand side evaluated to 4.79405126702 (Allowable error: 0.1%, Actual error: 2.4%) Warning: Constraint [SM_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0) + mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{... <= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0)...] is not tight because the left hand side evaluated to 4.73114636398 but the right hand side evaluated to 4.81373804347 (Allowable error: 0.1%, Actual error: 1.7%) Warning: Constraint [C_{L_{ht}}_Mission/CruiseSegment/CruiseP/AircraftP.1/HorizontalTailPerformance.1_(0, 0)*C_{L}_Missio... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(0, 0)...] is not tight because the left hand side evaluated to 7.60828745613 but the right hand side evaluated to 4.79405126702 (Allowable error: 0.1%, Actual error: 37%) Warning: Constraint [C_{L_{ht}}_Mission/CruiseSegment/CruiseP/AircraftP.1/HorizontalTailPerformance.1_(1, 0)*C_{L}_Missio... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0)...] is not tight because the left hand side evaluated to 7.5797125899 but the right hand side evaluated to 4.81373804347 (Allowable error: 0.1%, Actual error: 36%) Solves with these variables bounded: value near lower bound: [MaxClimbDistance_Mission, \bar{A}_{fuel, max}_Mission/Aircraft/Wing/WingNoStruct, CruiseAlt_Mission, ClimbDistance_Mission] value near upper bound: [TotalTime_Mission, A_{tri}_Mission/Aircraft/Wing/WingNoStruct] Checking for relaxed constants... WEIGHT DIFFERENCES Total Fuel Weight Percent Diff: [-6.97452411] Total Aircraft Weight Percent Diff: [-4.95042201] Engine Weight Percent Diff: -8.23501399456 Fuselage Weight Percent Diff: -10.9542224809 Payload Weight Percent Diff: [-0.04003556] VT Weight Percent Diff: -24.5188578268 HT Weight Percent Diff: -85.1524971105 Wing Weight Percent Diff: 0.426125998173 WING DIFFERENCES Wing Span Percent Diff: 0.921607178473 Wing Area Percent Diff: -6.86186365133 HORIZONTAL TAIL DIFFERENCES HT Area Percent Diff: -54.6184532079 VERTICAL TAIL DIFFERENCES VT Span Percent Diff: -16.3231630365 VT Area Percent Diff: -29.996920513 CRUISE SEGMENT 1 DRAG DIFFERENCES Overall Cd Percent Diff: [-0.13083537] Nacelle Cd Percent Diff: [ 23.80938431] HT Cd Percent Diff: [-63.50962662] dimensionless Fuselage Cd Percent Diff: [ 45.32349081] VT Cd Percent Diff: [ 60.36885157] dimensionless Induced Drag Cd Percent Diff: [ 1.06379293] Wing Profile Cd Percent Diff: [-15.69393029] CRUISE SEGMENT 1 TSFC DIFFERENCES Initial Cruise TSFC Percent Diff: [ 2.99108489] FUSELAGE DIFFERENCES Fan Propulsive Efficiency in Cruise Segment 1 --------------------- 0.790004720809 Beginning signomial solve. Solving took 7 GP solves and 69.4 seconds. Warning: Constraint [W_{avg}_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0)*x_{CG}_Mission/CruiseSegment/CruiseP/Aircra... >= 0.225*W_{ht}_Mission/Aircraft/HorizontalTail*x_{CG_{ht}}_Mission/Aircraft/HorizontalTail/HorizontalT...] is not tight because the left hand side evaluated to 2427091.05132 force_pound * meter but the right hand side evaluated to 2397884.83981 force_pound * meter (Allowable error: 0.1%, Actual error: 1.2%) Warning: Constraint [0.0417*S_Mission/Aircraft/Wing/WingNoStruct**-1*\tan(\Lambda)_Mission/Aircraft/Wing/WingNoStruct*b_M... >= \Delta x_{AC_{wing}}_Mission/Aircraft/Wing [m]...] is not tight because the left hand side evaluated to 2.21510282056 meter but the right hand side evaluated to 1.96468632198 meter (Allowable error: 0.1%, Actual error: 11%) Warning: Constraint [F_{6}_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(3, 0) + F_{8}_Mission/Aircraft/En... >= F_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(3, 0) [N]...] is not tight because the left hand side evaluated to 17472.5139616 newton but the right hand side evaluated to 17443.2145325 newton (Allowable error: 0.1%, Actual error: 0.17%) Warning: Constraint [-C_{p_{fuel}_Mission/Aircraft/Engine/Combustor*T_{t_f}_Mission/Aircraft/Engine/Combustor*f_Mission/A... <= \eta_{B}_Mission/Aircraft/Engine/Combustor*f_Mission/Aircraft/Engine/EnginePerformance/CombustorPerf...] is not tight because the left hand side evaluated to 1242108.05255 joule / kilogram but the right hand side evaluated to 1.48151077346 megajoule / kilogram (Allowable error: 0.1%, Actual error: 9.5%) Warning: Constraint [-C_{p_{fuel}_Mission/Aircraft/Engine/Combustor*T_{t_f}_Mission/Aircraft/Engine/Combustor*f_Mission/A... <= \eta_{B}_Mission/Aircraft/Engine/Combustor*f_Mission/Aircraft/Engine/EnginePerformance/CombustorPerf...] is not tight because the left hand side evaluated to 642492.385771 joule / kilogram but the right hand side evaluated to 0.643976760313 megajoule / kilogram (Allowable error: 0.1%, Actual error: 0.1%) Warning: Constraint [W_{lg}_Mission/Aircraft/LandingGear*x_{CG_{lg}}_Mission/Aircraft/LandingGear [N*m]... >= W_{mg}_Mission/Aircraft/LandingGear*x_m_Mission/Aircraft/LandingGear + W_{ng}_Mission/Aircraft/Landi...] is not tight because the left hand side evaluated to 271790.27498 meter * newton but the right hand side evaluated to 263035.490592 meter * newton (Allowable error: 1.0%, Actual error: 3.3%) Warning: Constraint [x_m_Mission/Aircraft/LandingGear [m]... >= x_{wing}_Mission/Aircraft/Fuselage [m]...] is not tight because the left hand side evaluated to 18.576010682 meter but the right hand side evaluated to 16.6120942606 meter (Allowable error: 0.1%, Actual error: 12%) Warning: Constraint [C_{L_{ht}}_Mission/ClimbSegment/ClimbP/AircraftP/HorizontalTailPerformance_(0, 0)*C_{L}_Mission/Clim... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/ClimbSegment/ClimbP/AircraftP_(0, 0)...] is not tight because the left hand side evaluated to 10.9552405826 but the right hand side evaluated to 4.85819028877 (Allowable error: 0.1%, Actual error: 56%) Warning: Constraint [C_{L_{ht}}_Mission/ClimbSegment/ClimbP/AircraftP/HorizontalTailPerformance_(1, 0)*C_{L}_Mission/Clim... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/ClimbSegment/ClimbP/AircraftP_(1, 0)...] is not tight because the left hand side evaluated to 10.0071288439 but the right hand side evaluated to 4.85820000516 (Allowable error: 0.1%, Actual error: 51%) Warning: Constraint [C_{L_{ht}}_Mission/ClimbSegment/ClimbP/AircraftP/HorizontalTailPerformance_(2, 0)*C_{L}_Mission/Clim... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/ClimbSegment/ClimbP/AircraftP_(2, 0)...] is not tight because the left hand side evaluated to 8.21527309964 but the right hand side evaluated to 4.85820000516 (Allowable error: 0.1%, Actual error: 41%) Warning: Constraint [0.25*\Delta x_{AC_{wing}}_Mission/Aircraft/Wing + x_{NP}_Mission/CruiseSegment/CruiseP/AircraftP.1_(... >= x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(0, 0) [m]...] is not tight because the left hand side evaluated to 18.6220443512 meter but the right hand side evaluated to 18.3758995683 meter (Allowable error: 0.1%, Actual error: 1.3%) Warning: Constraint [0.25*\Delta x_{AC_{wing}}_Mission/Aircraft/Wing + x_{NP}_Mission/CruiseSegment/CruiseP/AircraftP.1_(... >= x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0) [m]...] is not tight because the left hand side evaluated to 18.6220443512 meter but the right hand side evaluated to 18.4513585145 meter (Allowable error: 0.1%, Actual error: 0.92%) Warning: Constraint [SM_Mission/CruiseSegment/CruiseP/AircraftP.1_(0, 0) + mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{... <= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(0, 0)...] is not tight because the left hand side evaluated to 4.67771188026 but the right hand side evaluated to 4.79404249415 (Allowable error: 0.1%, Actual error: 2.4%) Warning: Constraint [SM_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0) + mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{... <= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0)...] is not tight because the left hand side evaluated to 4.73114083085 but the right hand side evaluated to 4.81372878996 (Allowable error: 0.1%, Actual error: 1.7%) Warning: Constraint [C_{L_{ht}}_Mission/CruiseSegment/CruiseP/AircraftP.1/HorizontalTailPerformance.1_(0, 0)*C_{L}_Missio... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(0, 0)...] is not tight because the left hand side evaluated to 7.60820611818 but the right hand side evaluated to 4.79404249415 (Allowable error: 0.1%, Actual error: 37%) Warning: Constraint [C_{L_{ht}}_Mission/CruiseSegment/CruiseP/AircraftP.1/HorizontalTailPerformance.1_(1, 0)*C_{L}_Missio... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/CruiseSegment/CruiseP/AircraftP.1_(1, 0)...] is not tight because the left hand side evaluated to 7.57970895155 but the right hand side evaluated to 4.81372878996 (Allowable error: 0.1%, Actual error: 36%) Solves with these variables bounded: value near lower bound: [MaxClimbDistance_Mission, \bar{A}_{fuel, max}_Mission/Aircraft/Wing/WingNoStruct, CruiseAlt_Mission, ClimbDistance_Mission] value near upper bound: [TotalTime_Mission, A_{tri}_Mission/Aircraft/Wing/WingNoStruct] Checking for relaxed constants... WEIGHT DIFFERENCES Total Fuel Weight Percent Diff: [-6.97422995] Total Aircraft Weight Percent Diff: [-4.95044675] Engine Weight Percent Diff: -8.23468392487 Fuselage Weight Percent Diff: -10.954618425 Payload Weight Percent Diff: [-0.04052335] VT Weight Percent Diff: -24.518327201 HT Weight Percent Diff: -85.1525242363 Wing Weight Percent Diff: 0.426467001174 WING DIFFERENCES Wing Span Percent Diff: 0.921619801497 Wing Area Percent Diff: -6.86162729346 HORIZONTAL TAIL DIFFERENCES HT Area Percent Diff: -54.6181566838 VERTICAL TAIL DIFFERENCES VT Span Percent Diff: -16.3229765607 VT Area Percent Diff: -29.9965958668 CRUISE SEGMENT 1 DRAG DIFFERENCES Overall Cd Percent Diff: [-0.12878397] Nacelle Cd Percent Diff: [ 23.80939215] HT Cd Percent Diff: [-63.50945817] dimensionless Fuselage Cd Percent Diff: [ 45.32347143] VT Cd Percent Diff: [ 60.36884608] dimensionless Induced Drag Cd Percent Diff: [ 1.06873722] Wing Profile Cd Percent Diff: [-15.69240054] CRUISE SEGMENT 1 TSFC DIFFERENCES Initial Cruise TSFC Percent Diff: [ 2.99029634] FUSELAGE DIFFERENCES Fan Propulsive Efficiency in Cruise Segment 1 --------------------- 0.790005398454