Passed
gpkit.tests.from_paths.TestFiles.test_SP_aircraft_py_mosek (from gpkit.tests.from_paths.TestFiles-20171101154919)
Standard Output
Beginning signomial solve. Solving took 7 GP solves and 8.74 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 2427080.58042 force_pound * meter but the right hand side evaluated to 2397884.70098 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 2.21510116766 meter but the right hand side evaluated to 1.96471397027 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 17472.5786819 newton but the right hand side evaluated to 17443.2465626 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 1242117.32303 joule / kilogram but the right hand side evaluated to 1.48135357457 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 642471.89935 joule / kilogram but the right hand side evaluated to 0.64395634391 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 271789.377607 meter * newton but the right hand side evaluated to 263034.79947 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 18.5759773038 meter but the right hand side evaluated to 16.6120350708 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 10.9551729 but the right hand side evaluated to 4.85819148138 (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 10.0069363245 but the right hand side evaluated to 4.8582017048 (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 8.21524795559 but the right hand side evaluated to 4.85820174366 (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 18.6219899576 meter but the right hand side evaluated to 18.3758572053 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 18.6219899576 meter but the right hand side evaluated to 18.4513132846 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 4.67771695761 but the right hand side evaluated to 4.79404507956 (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 4.73113921223 but the right hand side evaluated to 4.81373068341 (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 7.60828214703 but the right hand side evaluated to 4.79404507956 (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 7.57970548302 but the right hand side evaluated to 4.81373068341 (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: [-6.97455593] Total Aircraft Weight Percent Diff: [-4.9504413] Engine Weight Percent Diff: -8.23499469654 Fuselage Weight Percent Diff: -10.9542123114 Payload Weight Percent Diff: [-0.0400356] VT Weight Percent Diff: -24.5190658241 HT Weight Percent Diff: -85.152549248 Wing Weight Percent Diff: 0.42605631355 WING DIFFERENCES Wing Span Percent Diff: 0.921607331634 Wing Area Percent Diff: -6.86185184279 HORIZONTAL TAIL DIFFERENCES HT Area Percent Diff: -54.6185221232 VERTICAL TAIL DIFFERENCES VT Span Percent Diff: -16.3232315319 VT Area Percent Diff: -29.9970351182 CRUISE SEGMENT 1 DRAG DIFFERENCES Overall Cd Percent Diff: [-0.13079719] Nacelle Cd Percent Diff: [ 23.80940374] HT Cd Percent Diff: [-63.50969853] dimensionless Fuselage Cd Percent Diff: [ 45.32349081] VT Cd Percent Diff: [ 60.36852662] dimensionless Induced Drag Cd Percent Diff: [ 1.06393744] Wing Profile Cd Percent Diff: [-15.69388502] CRUISE SEGMENT 1 TSFC DIFFERENCES Initial Cruise TSFC Percent Diff: [ 2.99108368] FUSELAGE DIFFERENCES Fan Propulsive Efficiency in Cruise Segment 1 --------------------- 0.790004751898