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Passed
gpkit.tests.from_paths.TestFiles.test_SP_aircraft_py_mosek (from gpkit.tests.from_paths.TestFiles-20171016093834)
Standard Output
Beginning signomial solve.
Solving took 7 GP solves and 8.72 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 2427079.1154 force_pound * meter but the right hand side evaluated to 2397884.6535 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 2.21510116776 meter but the right hand side evaluated to 1.96471421268 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 17472.580014 newton but the right hand side evaluated to 17443.247308 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 1242117.37127 joule / kilogram but the right hand side evaluated to 1.48135516658 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 642471.583267 joule / kilogram but the right hand side evaluated to 0.643956081756 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 271789.676024 meter * newton but the right hand side evaluated to 263034.781643 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 18.5759770413 meter but the right hand side evaluated to 16.6120344693 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 10.9551731413 but the right hand side evaluated to 4.85819162885 (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 10.0069366754 but the right hand side evaluated to 4.8582018519 (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 8.21524805935 but the right hand side evaluated to 4.85820188787 (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 18.6219893681 meter but the right hand side evaluated to 18.3758563273 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 18.6219893681 meter but the right hand side evaluated to 18.4513094982 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 4.67771707402 but the right hand side evaluated to 4.79404513416 (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 4.73113716496 but the right hand side evaluated to 4.81372998041 (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 7.60828434873 but the right hand side evaluated to 4.79404513416 (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 7.57970300197 but the right hand side evaluated to 4.81372998041 (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: [-6.97455386]
Total Aircraft Weight Percent Diff: [-4.9504418]
Engine Weight Percent Diff: -8.23499669297
Fuselage Weight Percent Diff: -10.9542138449
Payload Weight Percent Diff: [-0.0400356]
VT Weight Percent Diff: -24.5190737152
HT Weight Percent Diff: -85.1525537388
Wing Weight Percent Diff: 0.426058031923
WING DIFFERENCES
Wing Span Percent Diff: 0.921607350726
Wing Area Percent Diff: -6.86185711352
HORIZONTAL TAIL DIFFERENCES
HT Area Percent Diff: -54.6185284229
VERTICAL TAIL DIFFERENCES
VT Span Percent Diff: -16.3232334483
VT Area Percent Diff: -29.9970383249
CRUISE SEGMENT 1 DRAG DIFFERENCES
Overall Cd Percent Diff: [-0.13085299]
Nacelle Cd Percent Diff: [ 23.80939441]
HT Cd Percent Diff: [-63.50970081] dimensionless
Fuselage Cd Percent Diff: [ 45.32349081]
VT Cd Percent Diff: [ 60.36853973] dimensionless
Induced Drag Cd Percent Diff: [ 1.06380269]
Wing Profile Cd Percent Diff: [-15.69392772]
CRUISE SEGMENT 1 TSFC DIFFERENCES
Initial Cruise TSFC Percent Diff: [ 2.99108438]
FUSELAGE DIFFERENCES
Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790004758366
Beginning signomial solve.
Solving took 7 GP solves and 11.1 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 2427083.77006 force_pound * meter but the right hand side evaluated to 2397878.14391 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 2.21510098519 meter but the right hand side evaluated to 1.96471795369 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 17472.4964891 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 642492.36616 joule / kilogram but the right hand side evaluated to 0.643976116336 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 271789.7314 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 16.6120444244 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 10.9552248455 but the right hand side evaluated to 4.8581805724 (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 10.0071246236 but the right hand side evaluated to 4.85819028877 (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 8.21526155098 but the right hand side evaluated to 4.85819028877 (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 18.6220024229 meter but the right hand side evaluated to 18.3758628166 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 18.6220024229 meter but the right hand side evaluated to 18.4513216119 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 4.67770643186 but the right hand side evaluated to 4.79403290607 (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 4.7311273671 but the right hand side evaluated to 4.81371916251 (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 7.60820099543 but the right hand side evaluated to 4.79403290607 (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 7.5796955958 but the right hand side evaluated to 4.81371916251 (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: -24.5186291271
HT Weight Percent Diff: -85.1525984735
Wing Weight Percent Diff: 0.425462741526
WING DIFFERENCES
Wing Span Percent Diff: 0.921619801497
Wing Area Percent Diff: -6.86153415504
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: [-0.12878397]
Nacelle Cd Percent Diff: [ 23.80939215]
HT Cd Percent Diff: [-63.50960413] dimensionless
Fuselage Cd Percent Diff: [ 45.32347143]
VT Cd Percent Diff: [ 60.36820461] dimensionless
Induced Drag Cd Percent Diff: [ 1.06883829]
Wing Profile Cd Percent Diff: [-15.69240054]
CRUISE SEGMENT 1 TSFC DIFFERENCES
Initial Cruise TSFC Percent Diff: [ 2.99028604]
FUSELAGE DIFFERENCES
Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790005398454