Passed
gpkit.tests.from_paths.TestFiles.test_SP_aircraft_py_mosek (from gpkit.tests.from_paths.TestFiles-20171013172831)
Standard Output
Beginning signomial solve. Solving took 7 GP solves and 6.85 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 2427085.85339 force_pound * meter but the right hand side evaluated to 2397885.5539 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 2.21510116743 meter but the right hand side evaluated to 1.96470529942 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 17472.58705 newton but the right hand side evaluated to 17443.2534188 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 1242117.24687 joule / kilogram but the right hand side evaluated to 1.48135574037 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 642471.508269 joule / kilogram but the right hand side evaluated to 0.643956067067 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 271789.576749 meter * newton but the right hand side evaluated to 263034.911512 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 18.5759817584 meter but the right hand side evaluated to 16.6120485458 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 10.9551788619 but the right hand side evaluated to 4.8581933941 (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 10.0069384027 but the right hand side evaluated to 4.85820362103 (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 8.21525188163 but the right hand side evaluated to 4.85820367921 (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 18.6220014463 meter but the right hand side evaluated to 18.3758668722 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 18.6220014463 meter but the right hand side evaluated to 18.4513320928 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 4.6777175842 but the right hand side evaluated to 4.79404659406 (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 4.73114648509 but the right hand side evaluated to 4.81373457865 (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 7.6082878315 but the right hand side evaluated to 4.79404659406 (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 7.57971405054 but the right hand side evaluated to 4.81373457865 (Allowable error: 0.1%, Actual error: 36%) Solves with these variables bounded: value near lower bound: [CruiseAlt_Mission] value near upper bound: [TotalTime_Mission, MaxClimbDistance_Mission, \bar{A}_{fuel, max}_Mission/Aircraft/Wing/WingNoStruct, A_{tri}_Mission/Aircraft/Wing/WingNoStruct, ClimbDistance_Mission] Checking for relaxed constants... WEIGHT DIFFERENCES Total Fuel Weight Percent Diff: [-6.97453107] Total Aircraft Weight Percent Diff: [-4.95042694] Engine Weight Percent Diff: -8.23497484908 Fuselage Weight Percent Diff: -10.9542138708 Payload Weight Percent Diff: [-0.04003558] VT Weight Percent Diff: -24.5189498798 HT Weight Percent Diff: -85.1525122683 Wing Weight Percent Diff: 0.426072095888 WING DIFFERENCES Wing Span Percent Diff: 0.921607251151 Wing Area Percent Diff: -6.86183222356 HORIZONTAL TAIL DIFFERENCES HT Area Percent Diff: -54.6184722737 VERTICAL TAIL DIFFERENCES VT Span Percent Diff: -16.3231930514 VT Area Percent Diff: -29.9969707333 CRUISE SEGMENT 1 DRAG DIFFERENCES Overall Cd Percent Diff: [-0.1309365] Nacelle Cd Percent Diff: [ 23.80935756] HT Cd Percent Diff: [-63.50965707] dimensionless Fuselage Cd Percent Diff: [ 45.32349081] VT Cd Percent Diff: [ 60.36868359] dimensionless Induced Drag Cd Percent Diff: [ 1.0636099] Wing Profile Cd Percent Diff: [-15.69400377] CRUISE SEGMENT 1 TSFC DIFFERENCES Initial Cruise TSFC Percent Diff: [ 2.99108557] FUSELAGE DIFFERENCES Fan Propulsive Efficiency in Cruise Segment 1 --------------------- 0.79000478441 Beginning signomial solve. Solving took 7 GP solves and 7.82 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 2427171.14665 force_pound * meter but the right hand side evaluated to 2397893.7729 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 2.21510126999 meter but the right hand side evaluated to 1.9643708187 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 17473.0353433 newton but the right hand side evaluated to 17443.5808438 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 1241928.20572 joule / kilogram but the right hand side evaluated to 1.47970443241 megajoule / kilogram (Allowable error: 0.1%, Actual error: 9.4%) 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 271791.633935 meter * newton but the right hand side evaluated to 263036.259643 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 18.5760478341 meter but the right hand side evaluated to 16.6124431182 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 10.9552162411 but the right hand side evaluated to 4.85828745355 (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 10.0062855225 but the right hand side evaluated to 4.85829717013 (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 8.21540276495 but the right hand side evaluated to 4.85829717013 (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 18.6223106879 meter but the right hand side evaluated to 18.3761017043 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 18.6223106879 meter but the right hand side evaluated to 18.4517275454 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 4.67775739464 but the right hand side evaluated to 4.79411919944 (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 4.73130037034 but the right hand side evaluated to 4.81384913468 (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 7.60869773654 but the right hand side evaluated to 4.79411919944 (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 7.57987941523 but the right hand side evaluated to 4.81384913468 (Allowable error: 0.1%, Actual error: 36%) Solves with these variables bounded: value near lower bound: [CruiseAlt_Mission] value near upper bound: [TotalTime_Mission, MaxClimbDistance_Mission, \bar{A}_{fuel, max}_Mission/Aircraft/Wing/WingNoStruct, A_{tri}_Mission/Aircraft/Wing/WingNoStruct, ClimbDistance_Mission] Checking for relaxed constants... WEIGHT DIFFERENCES Total Fuel Weight Percent Diff: [-6.97422995] Total Aircraft Weight Percent Diff: [-4.95044675] Engine Weight Percent Diff: -8.23596863031 Fuselage Weight Percent Diff: -10.954618425 Payload Weight Percent Diff: [-0.04052335] VT Weight Percent Diff: -24.5177233452 HT Weight Percent Diff: -85.150876075 Wing Weight Percent Diff: 0.426467001174 WING DIFFERENCES Wing Span Percent Diff: 0.921619801497 Wing Area Percent Diff: -6.86209298416 HORIZONTAL TAIL DIFFERENCES HT Area Percent Diff: -54.6177936276 VERTICAL TAIL DIFFERENCES VT Span Percent Diff: -16.3228092065 VT Area Percent Diff: -29.9962458489 CRUISE SEGMENT 1 DRAG DIFFERENCES Overall Cd Percent Diff: [-0.14126709] Nacelle Cd Percent Diff: [ 23.80753503] HT Cd Percent Diff: [-63.50898379] dimensionless Fuselage Cd Percent Diff: [ 45.32347143] VT Cd Percent Diff: [ 60.37333647] dimensionless Induced Drag Cd Percent Diff: [ 1.03872426] Wing Profile Cd Percent Diff: [-15.70226395] CRUISE SEGMENT 1 TSFC DIFFERENCES Initial Cruise TSFC Percent Diff: [ 2.99610516] FUSELAGE DIFFERENCES Fan Propulsive Efficiency in Cruise Segment 1 --------------------- 0.790008744115