Passed
gpkit.tests.from_paths.TestFiles.test_SP_aircraft_py_mosek_cli (from gpkit.tests.from_paths.TestFiles-20171018091937)
Standard Output
Beginning signomial solve. Solving took 7 GP solves and 9.07 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 2427085.98282 force_pound * meter but the right hand side evaluated to 2397886.33822 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 1.96469267969 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 17472.5856282 newton but the right hand side evaluated to 17443.2527458 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 1242117.31287 joule / kilogram but the right hand side evaluated to 1.48135612606 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 642471.423303 joule / kilogram but the right hand side evaluated to 0.643955939527 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 271789.909184 meter * newton but the right hand side evaluated to 263034.995277 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 18.5759877565 meter but the right hand side evaluated to 16.6120674423 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 10.9551828856 but the right hand side evaluated to 4.85819878552 (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 10.0069443228 but the right hand side evaluated to 4.85820900838 (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 8.21525670644 but the right hand side evaluated to 4.85820907832 (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 18.6220170358 meter but the right hand side evaluated to 18.3758795632 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 18.6220170358 meter but the right hand side evaluated to 18.451343234 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 4.67772091321 but the right hand side evaluated to 4.79405125443 (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 4.73114868225 but the right hand side evaluated to 4.81373884025 (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 7.6082869278 but the right hand side evaluated to 4.79405125443 (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 7.57971539139 but the right hand side evaluated to 4.81373884025 (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: [-6.97452972] Total Aircraft Weight Percent Diff: [-4.95042573] Engine Weight Percent Diff: -8.23502216663 Fuselage Weight Percent Diff: -10.9542231148 Payload Weight Percent Diff: [-0.04003556] VT Weight Percent Diff: -24.5188625449 HT Weight Percent Diff: -85.1524960736 Wing Weight Percent Diff: 0.426121810916 WING DIFFERENCES Wing Span Percent Diff: 0.921607179432 Wing Area Percent Diff: -6.86186123695 HORIZONTAL TAIL DIFFERENCES HT Area Percent Diff: -54.6184507874 VERTICAL TAIL DIFFERENCES VT Span Percent Diff: -16.3231647766 VT Area Percent Diff: -29.9969234246 CRUISE SEGMENT 1 DRAG DIFFERENCES Overall Cd Percent Diff: [-0.13082268] Nacelle Cd Percent Diff: [ 23.80937946] HT Cd Percent Diff: [-63.50962616] dimensionless Fuselage Cd Percent Diff: [ 45.32349081] VT Cd Percent Diff: [ 60.36883608] dimensionless Induced Drag Cd Percent Diff: [ 1.06382788] Wing Profile Cd Percent Diff: [-15.69391913] CRUISE SEGMENT 1 TSFC DIFFERENCES Initial Cruise TSFC Percent Diff: [ 2.99108521] FUSELAGE DIFFERENCES Fan Propulsive Efficiency in Cruise Segment 1 --------------------- 0.790004711802 Beginning signomial solve. Solving took 7 GP solves and 10.9 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 2427088.62423 force_pound * meter but the right hand side evaluated to 2397879.6581 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 2.2151029155 meter but the right hand side evaluated to 1.96470007484 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 17472.5034131 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 1242108.22434 joule / kilogram but the right hand side evaluated to 1.48151373649 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 271790.00319 meter * newton but the right hand side evaluated to 263034.971207 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 18.575992106 meter but the right hand side evaluated to 16.6120776485 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 10.9552358269 but the right hand side evaluated to 4.85818543058 (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 10.0071293742 but the right hand side evaluated to 4.85819514696 (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 8.21526767668 but the right hand side evaluated to 4.85819514696 (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 18.6220311773 meter but the right hand side evaluated to 18.3758811924 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 18.6220311773 meter but the right hand side evaluated to 18.4513400632 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 4.67771149492 but the right hand side evaluated to 4.79403770011 (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 4.7311359173 but the right hand side evaluated to 4.81372397623 (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 7.60820548166 but the right hand side evaluated to 4.79403770011 (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 7.57970439129 but the right hand side evaluated to 4.81372397623 (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: -24.5184781642 HT Weight Percent Diff: -85.1525687786 Wing Weight Percent Diff: 0.425462741526 WING DIFFERENCES Wing Span Percent Diff: 0.921619801497 Wing Area Percent Diff: -6.86162729346 HORIZONTAL TAIL DIFFERENCES HT Area Percent Diff: -54.6182020656 VERTICAL TAIL DIFFERENCES VT Span Percent Diff: -16.3230602377 VT Area Percent Diff: -29.9966658701 CRUISE SEGMENT 1 DRAG DIFFERENCES Overall Cd Percent Diff: [-0.12878397] Nacelle Cd Percent Diff: [ 23.80939215] HT Cd Percent Diff: [-63.50953115] dimensionless Fuselage Cd Percent Diff: [ 45.32347143] VT Cd Percent Diff: [ 60.36852535] 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