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Passed
gpkit.tests.from_paths.TestFiles.test_SPaircraft_py_mosek (from gpkit.tests.from_paths.TestFiles-20180627132737)
Standard Output
Beginning signomial solve.
Using solver 'mosek'
Solving for 1776 variables.
Solving took 5.72 seconds.
Using solver 'mosek'
Solving for 1776 variables.
Solving took 10.9 seconds.
Using solver 'mosek'
Solving for 1776 variables.
Solving took 11.3 seconds.
Using solver 'mosek'
Solving for 1776 variables.
Solving took 8.68 seconds.
Using solver 'mosek'
Solving for 1776 variables.
Solving took 10.4 seconds.
Using solver 'mosek'
Solving for 1776 variables.
Solving took 9.22 seconds.
Using solver 'mosek'
Solving for 1776 variables.
Solving took 5.41 seconds.
Using solver 'mosek'
Solving for 1776 variables.
Solving took 7.5 seconds.
Using solver 'mosek'
Solving for 1776 variables.
Solving took 10.4 seconds.
Solving took 9 GP solves and 93.9 seconds.
Warning: Constraint [W_{avg}_Mission/FlightSegment/FlightP/AircraftP_(4, 0)*x_{CG}_Mission/FlightSegment/FlightP/Aircraft... >= 0.225*W_{ht}_Mission/Aircraft/HorizontalTail*x_{CG_{ht}}_Mission/Aircraft/HorizontalTail/HorizontalT...] is not tight because the left hand side evaluated to 2150734.50729 force_pound * meter but the right hand side evaluated to 2110367.24783 force_pound * meter (Allowable error: 0.1%, Actual error: 1.9%)
Warning: Constraint [W_{pass}_Mission/Aircraft/Fuselage_(0,) [lbf]... >= W_{avg. pass}_Mission/Aircraft/Fuselage*n_{pass}_Mission/Aircraft/Fuselage_(0,) [lbf]...] is not tight because the left hand side evaluated to 32774.3684813 force_pound but the right hand side evaluated to 32399.999998 force_pound (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 2.21510116778 meter but the right hand side evaluated to 1.56569286873 meter (Allowable error: 0.1%, Actual error: 29%)
Warning: Constraint [F_{6}_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(0, 0) + F_{8}_Mission/Aircraft/En... >= F_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(0, 0) [N]...] is not tight because the left hand side evaluated to 37402.9328655 newton but the right hand side evaluated to 37221.7192295 newton (Allowable error: 0.1%, Actual error: 0.48%)
Warning: Constraint [F_{6}_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(1, 0) + F_{8}_Mission/Aircraft/En... >= F_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(1, 0) [N]...] is not tight because the left hand side evaluated to 40681.6492938 newton but the right hand side evaluated to 40621.049629 newton (Allowable error: 0.1%, Actual error: 0.15%)
Warning: Constraint [F_{6}_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(2, 0) + F_{8}_Mission/Aircraft/En... >= F_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(2, 0) [N]...] is not tight because the left hand side evaluated to 27841.4508828 newton but the right hand side evaluated to 27789.1341043 newton (Allowable error: 0.1%, Actual error: 0.19%)
Warning: Constraint [F_{6}_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(4, 0) + F_{8}_Mission/Aircraft/En... >= F_Mission/Aircraft/Engine/EnginePerformance/ThrustPerformance_(4, 0) [N]...] is not tight because the left hand side evaluated to 12415.2656378 newton but the right hand side evaluated to 12373.9454598 newton (Allowable error: 0.1%, Actual error: 0.33%)
Warning: Constraint [-M_{takeoff}_Mission/Aircraft/Engine/EngineConstants*\eta_{HPshaft}_Mission/Aircraft/Engine/Turbine*... >= -h_{t_{2.5}}_Mission/Aircraft/Engine/EnginePerformance/CompressorPerformance_(0, 0) + h_{t_3}_Missio...] is not tight because the left hand side evaluated to 147031.914411 joule / kilogram but the right hand side evaluated to 142869.478697 joule / kilogram (Allowable error: 0.1%, Actual error: 0.17%)
Warning: Constraint [x_m_Mission/Aircraft/LandingGear [m]... >= x_{wing}_Mission/Aircraft/Fuselage [m]...] is not tight because the left hand side evaluated to 18.9006972508 meter but the right hand side evaluated to 17.3409039473 meter (Allowable error: 0.1%, Actual error: 9%)
Warning: Constraint [0.25*\Delta x_{AC_{wing}}_Mission/Aircraft/Wing + x_{NP}_Mission/FlightSegment/FlightP/AircraftP_(0,... >= x_{AC}_Mission/FlightSegment/FlightP/AircraftP_(0, 0) [m]...] is not tight because the left hand side evaluated to 19.2489194475 meter but the right hand side evaluated to 19.1427988863 meter (Allowable error: 0.1%, Actual error: 0.55%)
Warning: Constraint [0.25*\Delta x_{AC_{wing}}_Mission/Aircraft/Wing + x_{NP}_Mission/FlightSegment/FlightP/AircraftP_(1,... >= x_{AC}_Mission/FlightSegment/FlightP/AircraftP_(1, 0) [m]...] is not tight because the left hand side evaluated to 19.2489194475 meter but the right hand side evaluated to 19.1426808683 meter (Allowable error: 0.1%, Actual error: 0.55%)
Warning: Constraint [0.25*\Delta x_{AC_{wing}}_Mission/Aircraft/Wing + x_{NP}_Mission/FlightSegment/FlightP/AircraftP_(2,... >= x_{AC}_Mission/FlightSegment/FlightP/AircraftP_(2, 0) [m]...] is not tight because the left hand side evaluated to 19.2489194475 meter but the right hand side evaluated to 19.1425600822 meter (Allowable error: 0.1%, Actual error: 0.55%)
Warning: Constraint [0.25*\Delta x_{AC_{wing}}_Mission/Aircraft/Wing + x_{NP}_Mission/FlightSegment/FlightP/AircraftP_(3,... >= x_{AC}_Mission/FlightSegment/FlightP/AircraftP_(3, 0) [m]...] is not tight because the left hand side evaluated to 19.2489194475 meter but the right hand side evaluated to 18.910868125 meter (Allowable error: 0.1%, Actual error: 1.8%)
Warning: Constraint [0.25*\Delta x_{AC_{wing}}_Mission/Aircraft/Wing + x_{NP}_Mission/FlightSegment/FlightP/AircraftP_(4,... >= x_{AC}_Mission/FlightSegment/FlightP/AircraftP_(4, 0) [m]...] is not tight because the left hand side evaluated to 19.2489194475 meter but the right hand side evaluated to 19.019826162 meter (Allowable error: 0.1%, Actual error: 1.2%)
Warning: Constraint [-mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{CG}_Mission/FlightSegment/FlightP/AircraftP_(0, 0) + ... >= SM_Mission/FlightSegment/FlightP/AircraftP_(0, 0)...] is not tight because the left hand side evaluated to 0.2244664719353393 but the right hand side evaluated to 0.17208944123351777 (Allowable error: 0.1%, Actual error: 1%)
Warning: Constraint [-mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{CG}_Mission/FlightSegment/FlightP/AircraftP_(1, 0) + ... >= SM_Mission/FlightSegment/FlightP/AircraftP_(1, 0)...] is not tight because the left hand side evaluated to 0.22443561603363182 but the right hand side evaluated to 0.17208124518842563 (Allowable error: 0.1%, Actual error: 1%)
Warning: Constraint [-mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{CG}_Mission/FlightSegment/FlightP/AircraftP_(2, 0) + ... >= SM_Mission/FlightSegment/FlightP/AircraftP_(2, 0)...] is not tight because the left hand side evaluated to 0.22440397337231893 but the right hand side evaluated to 0.1720727617993469 (Allowable error: 0.1%, Actual error: 1%)
Warning: Constraint [-mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{CG}_Mission/FlightSegment/FlightP/AircraftP_(3, 0) + ... >= SM_Mission/FlightSegment/FlightP/AircraftP_(3, 0)...] is not tight because the left hand side evaluated to 0.3589202236506246 but the right hand side evaluated to 0.20338062232598672 (Allowable error: 0.1%, Actual error: 3.1%)
Warning: Constraint [-mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{CG}_Mission/FlightSegment/FlightP/AircraftP_(4, 0) + ... >= SM_Mission/FlightSegment/FlightP/AircraftP_(4, 0)...] is not tight because the left hand side evaluated to 0.2989192873904037 but the right hand side evaluated to 0.19039126758218822 (Allowable error: 0.1%, Actual error: 2.2%)
Warning: Constraint [C_{L_{ht}}_Mission/FlightSegment/FlightP/AircraftP/HorizontalTailPerformance_(0, 0)*C_{L}_Mission/Fl... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/FlightSegment/FlightP/AircraftP_(0, 0)...] is not tight because the left hand side evaluated to 11.936857727592438 but the right hand side evaluated to 5.010011887258814 (Allowable error: 0.1%, Actual error: 58%)
Warning: Constraint [C_{L_{ht}}_Mission/FlightSegment/FlightP/AircraftP/HorizontalTailPerformance_(1, 0)*C_{L}_Mission/Fl... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/FlightSegment/FlightP/AircraftP_(1, 0)...] is not tight because the left hand side evaluated to 10.02902541797267 but the right hand side evaluated to 5.0099809998611 (Allowable error: 0.1%, Actual error: 50%)
Warning: Constraint [C_{L_{ht}}_Mission/FlightSegment/FlightP/AircraftP/HorizontalTailPerformance_(2, 0)*C_{L}_Mission/Fl... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/FlightSegment/FlightP/AircraftP_(2, 0)...] is not tight because the left hand side evaluated to 8.914454536701848 but the right hand side evaluated to 5.00994938798438 (Allowable error: 0.1%, Actual error: 44%)
Warning: Constraint [C_{L_{ht}}_Mission/FlightSegment/FlightP/AircraftP/HorizontalTailPerformance_(3, 0)*C_{L}_Mission/Fl... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/FlightSegment/FlightP/AircraftP_(3, 0)...] is not tight because the left hand side evaluated to 7.694898434911709 but the right hand side evaluated to 4.94931147046969 (Allowable error: 0.1%, Actual error: 36%)
Warning: Constraint [C_{L_{ht}}_Mission/FlightSegment/FlightP/AircraftP/HorizontalTailPerformance_(4, 0)*C_{L}_Mission/Fl... >= mac_Mission/Aircraft/Wing/WingNoStruct**-1*x_{AC}_Mission/FlightSegment/FlightP/AircraftP_(4, 0)...] is not tight because the left hand side evaluated to 7.701433408512286 but the right hand side evaluated to 4.977827732053454 (Allowable error: 0.1%, Actual error: 35%)
Solves with these variables bounded:
value near lower bound: CruiseAlt_Mission
value near upper bound: TotalTime_Mission, \alpha_{max}_Mission/Aircraft/Engine/Thrust, A_{tri}_Mission/Aircraft/Wing/WingNoStruct
Checking for relaxed constants...
WEIGHT DIFFERENCES
Total Fuel Weight Percent Diff: [-34.04351932]
Total Aircraft Weight Percent Diff: [-16.3663436]
Engine Weight Percent Diff: -7.907547951363673
Fuselage Weight Percent Diff: -7.482852308298594
Payload Weight Percent Diff: [-0.04003562]
VT Weight Percent Diff: -34.04958851586023
HT Weight Percent Diff: -74.89597082420508
Wing Weight Percent Diff: -0.786818266435354
WING DIFFERENCES
Wing Span Percent Diff: 3.4458470835791974
Wing Area Percent Diff: -2.4553717514970326
HORIZONTAL TAIL DIFFERENCES
HT Area Percent Diff: -33.30694781774727
VERTICAL TAIL DIFFERENCES
VT Span Percent Diff: -20.008619218683176
VT Area Percent Diff: -36.018620022684466
CRUISE SEGMENT 1 DRAG DIFFERENCES
L/D Percent Diff: [26.40555618]
Overall Cd Percent Diff: [-8.00043808]
Nacelle Cd Percent Diff: [-40.95170102]
HT Cd Percent Diff: [-49.67499172] dimensionless
Fuselage Cd Percent Diff: [38.24781523]
VT Cd Percent Diff: [34.05392651] dimensionless
Induced Drag Cd Percent Diff: [2.43781638]
Wing Profile Cd Percent Diff: [-13.35364395]
CRUISE SEGMENT 1 TSFC DIFFERENCES
Initial Cruise TSFC Percent Diff: [-8.59706695]
FUSELAGE DIFFERENCES
Weight of HB material: -58.34880393208362
Weight of VB material: -59.94821041293828
Fan Propulsive Efficiency in Cruise Segment 1
---------------------
[0.66542152]