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Passed
gpkit.tests.from_paths.TestFiles.test_SP_aircraft_py_mosek (from gpkit.tests.from_paths.TestFiles-20171018092256)
Standard Output
Beginning signomial solve.
Solving took 7 GP solves and 8.37 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 2427083.9769 force_pound * meter but the right hand side evaluated to 2397885.65864 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 2.21510116749 meter but the right hand side evaluated to 1.96470107952 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 17472.5827435 newton but the right hand side evaluated to 17443.2501569 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 1242117.26746 joule / kilogram but the right hand side evaluated to 1.48135511364 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 642471.574543 joule / kilogram but the right hand side evaluated to 0.643956067344 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 271789.778951 meter * newton but the right hand side evaluated to 263034.918649 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 18.5759832508 meter but the right hand side evaluated to 16.612054207 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 10.9551788969 but the right hand side evaluated to 4.85819597848 (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 10.0069414486 but the right hand side evaluated to 4.85820620088 (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 8.21525318576 but the right hand side evaluated to 4.85820625434 (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 18.622005853 meter but the right hand side evaluated to 18.3758700815 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 18.622005853 meter but the right hand side evaluated to 18.4513312731 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 4.67771937404 but the right hand side evaluated to 4.79404883458 (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 4.73114528789 but the right hand side evaluated to 4.8137357738 (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 7.60828485538 but the right hand side evaluated to 4.79404883458 (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 7.5797118663 but the right hand side evaluated to 4.8137357738 (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: [-6.97454126]
Total Aircraft Weight Percent Diff: [-4.9504323]
Engine Weight Percent Diff: -8.23500939186
Fuselage Weight Percent Diff: -10.9542197561
Payload Weight Percent Diff: [-0.04003558]
VT Weight Percent Diff: -24.5189506193
HT Weight Percent Diff: -85.1525221351
Wing Weight Percent Diff: 0.426096806481
WING DIFFERENCES
Wing Span Percent Diff: 0.921607255783
Wing Area Percent Diff: -6.86186089775
HORIZONTAL TAIL DIFFERENCES
HT Area Percent Diff: -54.6184834356
VERTICAL TAIL DIFFERENCES
VT Span Percent Diff: -16.3231931441
VT Area Percent Diff: -29.9969708885
CRUISE SEGMENT 1 DRAG DIFFERENCES
Overall Cd Percent Diff: [-0.13080581]
Nacelle Cd Percent Diff: [ 23.80939627]
HT Cd Percent Diff: [-63.50965743] dimensionless
Fuselage Cd Percent Diff: [ 45.32349081]
VT Cd Percent Diff: [ 60.36871045] dimensionless
Induced Drag Cd Percent Diff: [ 1.06388375]
Wing Profile Cd Percent Diff: [-15.69390015]
CRUISE SEGMENT 1 TSFC DIFFERENCES
Initial Cruise TSFC Percent Diff: [ 2.991084]
FUSELAGE DIFFERENCES
Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790004726867
Beginning signomial solve.
Solving took 7 GP solves and 9.83 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 2397882.82546 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 2.21510108013 meter but the right hand side evaluated to 1.96470086072 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 17472.4547829 newton but the right hand side evaluated to 17443.1447597 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 1242169.69383 joule / kilogram but the right hand side evaluated to 1.48194491972 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 642492.766804 joule / kilogram but the right hand side evaluated to 0.643983844096 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 263035.220871 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 16.6120776485 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 10.9552374929 but the right hand side evaluated to 4.85820000516 (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 10.0071653156 but the right hand side evaluated to 4.85820972157 (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 8.21525395316 but the right hand side evaluated to 4.85820972157 (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 18.6220303106 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 18.6220303106 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 4.677720465 but the right hand side evaluated to 4.79405208224 (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 4.73114974591 but the right hand side evaluated to 4.81373841742 (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 7.60819852957 but the right hand side evaluated to 4.79405208224 (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 7.57971713396 but the right hand side evaluated to 4.81373841742 (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: -8.23532627984
Fuselage Weight Percent Diff: -10.954618425
Payload Weight Percent Diff: [-0.04052335]
VT Weight Percent Diff: -24.5185536457
HT Weight Percent Diff: -85.1526430156
Wing Weight Percent Diff: 0.426467001174
WING DIFFERENCES
Wing Span Percent Diff: 0.921619801497
Wing Area Percent Diff: -6.86172043179
HORIZONTAL TAIL DIFFERENCES
HT Area Percent Diff: -54.6182928291
VERTICAL TAIL DIFFERENCES
VT Span Percent Diff: -16.3230602377
VT Area Percent Diff: -29.9967358734
CRUISE SEGMENT 1 DRAG DIFFERENCES
Overall Cd Percent Diff: [-0.12848436]
Nacelle Cd Percent Diff: [ 23.80902073]
HT Cd Percent Diff: [-63.50956764] dimensionless
Fuselage Cd Percent Diff: [ 45.32347143]
VT Cd Percent Diff: [ 60.36852535] dimensionless
Induced Drag Cd Percent Diff: [ 1.06964684]
Wing Profile Cd Percent Diff: [-15.691979]
CRUISE SEGMENT 1 TSFC DIFFERENCES
Initial Cruise TSFC Percent Diff: [ 2.98961661]
FUSELAGE DIFFERENCES
Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790003486651