Passed
gpkit.tests.from_paths.TestFiles.test_SP_aircraft_py_mosek (from gpkit.tests.from_paths.TestFiles-20171016094320)
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 2427085.19169 force_pound * meter but the right hand side evaluated to 2397885.75608 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 2.21510116745 meter but the right hand side evaluated to 1.96470064048 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 17472.5846028 newton but the right hand side evaluated to 17443.2516413 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 1242117.43657 joule / kilogram but the right hand side evaluated to 1.48135654322 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 642471.481438 joule / kilogram but the right hand side evaluated to 0.643956004088 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 271789.783254 meter * newton but the right hand side evaluated to 263034.933642 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 18.5759836113 meter but the right hand side evaluated to 16.6120550662 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 10.9551794133 but the right hand side evaluated to 4.85819615609 (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 10.0069412845 but the right hand side evaluated to 4.85820637885 (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 8.21525350888 but the right hand side evaluated to 4.85820643484 (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 18.622006611 meter but the right hand side evaluated to 18.3758708487 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 18.622006611 meter but the right hand side evaluated to 18.451334371 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 4.67771950554 but the right hand side evaluated to 4.79404902461 (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 4.73114712696 but the right hand side evaluated to 4.81373657185 (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 7.60828663435 but the right hand side evaluated to 4.79404902461 (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 7.57971403492 but the right hand side evaluated to 4.81373657185 (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: [-6.97453477] Total Aircraft Weight Percent Diff: [-4.95042911] Engine Weight Percent Diff: -8.23500737592 Fuselage Weight Percent Diff: -10.9542188464 Payload Weight Percent Diff: [-0.04003558] VT Weight Percent Diff: -24.5189376802 HT Weight Percent Diff: -85.1525170608 Wing Weight Percent Diff: 0.426100772054 WING DIFFERENCES Wing Span Percent Diff: 0.921607242804 Wing Area Percent Diff: -6.8618609293 HORIZONTAL TAIL DIFFERENCES HT Area Percent Diff: -54.6184811304 VERTICAL TAIL DIFFERENCES VT Span Percent Diff: -16.3231890726 VT Area Percent Diff: -29.9969640762 CRUISE SEGMENT 1 DRAG DIFFERENCES Overall Cd Percent Diff: [-0.13085172] Nacelle Cd Percent Diff: [ 23.80938521] HT Cd Percent Diff: [-63.5096541] dimensionless Fuselage Cd Percent Diff: [ 45.32349081] VT Cd Percent Diff: [ 60.36873778] dimensionless Induced Drag Cd Percent Diff: [ 1.06377439] Wing Profile Cd Percent Diff: [-15.69393695] CRUISE SEGMENT 1 TSFC DIFFERENCES Initial Cruise TSFC Percent Diff: [ 2.99108432] FUSELAGE DIFFERENCES Fan Propulsive Efficiency in Cruise Segment 1 --------------------- 0.790004737632 Beginning signomial solve. Solving took 7 GP solves and 10.7 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 2397878.94546 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 2.21510079533 meter but the right hand side evaluated to 1.96471088072 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 1242107.96665 joule / kilogram but the right hand side evaluated to 1.48150929195 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 271789.7314 meter * newton but the right hand side evaluated to 263034.977892 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 10.9552311164 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 10.0071246438 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 18.6220172667 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 18.6220172667 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 4.67770662453 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 4.73112754951 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 7.60820162007 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 7.5796952927 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: -24.5185536457 HT Weight Percent Diff: -85.152583626 Wing Weight Percent Diff: 0.425462741526 WING DIFFERENCES Wing Span Percent Diff: 0.921619801497 Wing Area Percent Diff: -6.86153415504 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: [-0.12888384] 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: [ 1.06873722] 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