Skip to content
[Jenkins]Jenkins
log in

Passed

gpkit.tests.from_paths.TestFiles.test_SP_aircraft_py_mosek (from gpkit.tests.from_paths.TestFiles-20171025140229)

Took 15 sec.

Standard Output

Beginning signomial solve.
Solving took 7 GP solves and 10.8 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 2427081.02913 force_pound * meter but the right hand side evaluated to 2397884.92238 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 2.21510116771 meter but the right hand side evaluated to 1.96471091786 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 17472.581999 newton but the right hand side evaluated to 17443.2490009 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 1242117.47361 joule / kilogram but the right hand side evaluated to 1.48135635226 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 642471.555826 joule / kilogram but the right hand side evaluated to 0.643956080076 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 271789.58168 meter * newton but the right hand side evaluated to 263034.822337 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 18.575978426 meter but the right hand side evaluated to 16.6120392036 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 10.955175094 but the right hand side evaluated to 4.85819286676 (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 10.0069377019 but the right hand side evaluated to 4.8582030893 (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 8.21524958505 but the right hand side evaluated to 4.85820312711 (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 18.6219932532 meter but the right hand side evaluated to 18.3758590978 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 18.6219932532 meter but the right hand side evaluated to 18.4513158118 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 4.67771769182 but the right hand side evaluated to 4.79404608647 (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 4.73114032506 but the right hand side evaluated to 4.81373185803 (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 7.60828607744 but the right hand side evaluated to 4.79404608647 (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 7.57970662212 but the right hand side evaluated to 4.81373185803 (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: [-6.97454735]


Total Aircraft Weight Percent Diff: [-4.95043775]


Engine Weight Percent Diff: -8.23499779359


Fuselage Weight Percent Diff: -10.9542151085


Payload Weight Percent Diff: [-0.0400356]


VT Weight Percent Diff: -24.5190429797


HT Weight Percent Diff: -85.1525464531


Wing Weight Percent Diff: 0.426071092114




WING DIFFERENCES


Wing Span Percent Diff: 0.921607336839


Wing Area Percent Diff: -6.86186173975




HORIZONTAL TAIL DIFFERENCES


HT Area Percent Diff: -54.6185210948




VERTICAL TAIL DIFFERENCES




VT Span Percent Diff: -16.3232228414


VT Area Percent Diff: -29.9970205776




CRUISE SEGMENT 1 DRAG DIFFERENCES


Overall Cd Percent Diff: [-0.13088183]


Nacelle Cd Percent Diff: [ 23.80938771]


HT Cd Percent Diff: [-63.50969139] dimensionless


Fuselage Cd Percent Diff: [ 45.32349081]


VT Cd Percent Diff: [ 60.3686003] dimensionless


Induced Drag Cd Percent Diff: [ 1.06372433]


Wing Profile Cd Percent Diff: [-15.69395244]




CRUISE SEGMENT 1 TSFC DIFFERENCES


Initial Cruise TSFC Percent Diff: [ 2.99108414]




FUSELAGE DIFFERENCES


Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790004766968

Standard Error