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Passed
gpkit.tests.from_paths.TestFiles.test_SP_aircraft_py_mosek (from gpkit.tests.from_paths.TestFiles-20171016203333)
Standard Output
Beginning signomial solve.
Solving took 7 GP solves and 31.2 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 2427079.05341 force_pound * meter but the right hand side evaluated to 2397885.60935 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 2.21510116744 meter but the right hand side evaluated to 1.96470305248 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 17472.5843457 newton but the right hand side evaluated to 17443.2514001 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 1242117.48852 joule / kilogram but the right hand side evaluated to 1.48135621057 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 642471.430057 joule / kilogram but the right hand side evaluated to 0.64395594674 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 271789.798363 meter * newton but the right hand side evaluated to 263034.92027 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 18.5759827201 meter but the right hand side evaluated to 16.6120518295 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 10.9551780441 but the right hand side evaluated to 4.85819494985 (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 10.0069397588 but the right hand side evaluated to 4.85820517362 (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 8.21525230325 but the right hand side evaluated to 4.85820523006 (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 18.6220040522 meter but the right hand side evaluated to 18.3758687213 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 18.6220040522 meter but the right hand side evaluated to 18.451319281 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 4.67771867533 but the right hand side evaluated to 4.79404794419 (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 4.73113698617 but the right hand side evaluated to 4.8137321075 (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 7.60828606842 but the right hand side evaluated to 4.79404794419 (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 7.57970215372 but the right hand side evaluated to 4.8137321075 (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: [-6.97453438]
Total Aircraft Weight Percent Diff: [-4.95042979]
Engine Weight Percent Diff: -8.23500415796
Fuselage Weight Percent Diff: -10.9542159667
Payload Weight Percent Diff: [-0.04003558]
VT Weight Percent Diff: -24.5189510456
HT Weight Percent Diff: -85.1525152147
Wing Weight Percent Diff: 0.426088647416
WING DIFFERENCES
Wing Span Percent Diff: 0.921607240519
Wing Area Percent Diff: -6.86185076619
HORIZONTAL TAIL DIFFERENCES
HT Area Percent Diff: -54.6184798626
VERTICAL TAIL DIFFERENCES
VT Span Percent Diff: -16.3231941378
VT Area Percent Diff: -29.9969725511
CRUISE SEGMENT 1 DRAG DIFFERENCES
Overall Cd Percent Diff: [-0.13085823]
Nacelle Cd Percent Diff: [ 23.80937862]
HT Cd Percent Diff: [-63.50965746] dimensionless
Fuselage Cd Percent Diff: [ 45.32349081]
VT Cd Percent Diff: [ 60.36869804] dimensionless
Induced Drag Cd Percent Diff: [ 1.06377352]
Wing Profile Cd Percent Diff: [-15.69394141]
CRUISE SEGMENT 1 TSFC DIFFERENCES
Initial Cruise TSFC Percent Diff: [ 2.99108567]
FUSELAGE DIFFERENCES
Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790004734279
Beginning signomial solve.
Solving took 7 GP solves and 11.6 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 2427086.19714 force_pound * meter but the right hand side evaluated to 2397878.88462 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 1.96470832659 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 17472.4999511 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 1242107.88076 joule / kilogram but the right hand side evaluated to 1.48150781044 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 16.6120610364 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 10.9552358245 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 10.0071246438 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 8.21526226574 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 18.6220164763 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 18.6220164763 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 4.67770662453 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 4.73113191581 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 7.60820130775 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 7.57969984142 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: -24.5185536457
HT Weight Percent Diff: -85.152583626
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: -54.6182474474
VERTICAL TAIL DIFFERENCES
VT Span Percent Diff: -16.3230602377
VT Area Percent Diff: -29.9967358734
CRUISE SEGMENT 1 DRAG DIFFERENCES
Overall Cd Percent Diff: [-0.12888384]
Nacelle Cd Percent Diff: [ 23.80939215]
HT Cd Percent Diff: [-63.50956764] dimensionless
Fuselage Cd Percent Diff: [ 45.32347143]
VT Cd Percent Diff: [ 60.36836498] 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