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Passed
gpkit.tests.from_paths.TestFiles.test_SPaircraft_py_mosek (from gpkit.tests.from_paths.TestFiles-20200227165108)
Standard Output
Beginning signomial solve. Using solver 'mosek' Solving for 1769 variables. Solving took 0.215 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.362 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.275 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.291 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.303 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.41 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.403 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.372 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.321 seconds. Solving took 9 GP solves and 11.3 seconds. Checking for relaxed constants... Solution check warning: sum of nu^T * A did not vanish Solution check warning: sum of nu^T * A did not vanish All relaxations are tight during final GP solve! WEIGHT DIFFERENCES Total Fuel Weight Percent Diff: [-14.73835942] Total Aircraft Weight Percent Diff: [-3.61468684] Engine Weight Percent Diff: -52.48002894453025 Fuselage Weight Percent Diff: 2.6372825332577805 Payload Weight Percent Diff: [-0.04003545] VT Weight Percent Diff: 27.167534778321574 HT Weight Percent Diff: -92.35265645105495 Wing Weight Percent Diff: 9.425648627389378 WING DIFFERENCES Wing Span Percent Diff: -0.029992588230377877 Wing Area Percent Diff: 33.190614625968166 HORIZONTAL TAIL DIFFERENCES HT Area Percent Diff: 45.87610493979715 VERTICAL TAIL DIFFERENCES VT Span Percent Diff: -0.6648730734349121 VT Area Percent Diff: -50.62770878861349 CRUISE SEGMENT 1 DRAG DIFFERENCES Overall Cd Percent Diff: [-12.9730021] L/D Percent Diff: [19.86274771] Nacelle Cd Percent Diff: [-32.80061821] HT Cd Percent Diff: [-79.14268218] dimensionless Fuselage Cd Percent Diff: [108.78752887] VT Cd Percent Diff: [-46.05853643] dimensionless Wing Cd percent Diff: [-13.30132119] Induced Drag Cd Percent Diff: [8.17418606] CRUISE SEGMENT 1 TSFC DIFFERENCES Initial Cruise TSFC Percent Diff: [-2.16434763] FUSELAGE DIFFERENCES Weight of HB material: -29.15397998198519 Weight of VB material: 135.1273813523209 Fan Propulsive Efficiency in Cruise Segment 1 --------------------- [0.68225992] Beginning signomial solve. Using solver 'mosek' Solving for 1769 variables. Solving took 0.189 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.375 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.244 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.329 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.258 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.4 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.358 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.325 seconds. Using solver 'mosek' Solving for 1769 variables. Solving took 0.333 seconds. Solving took 9 GP solves and 11.6 seconds. Checking for relaxed constants... All relaxations are tight during final GP solve! WEIGHT DIFFERENCES Total Fuel Weight Percent Diff: [-14.73841314] Total Aircraft Weight Percent Diff: [-3.61470144] Engine Weight Percent Diff: -52.47997030239334 Fuselage Weight Percent Diff: 2.637254301101981 Payload Weight Percent Diff: [-0.04003553] VT Weight Percent Diff: 27.167112517790194 HT Weight Percent Diff: -92.35271409869725 Wing Weight Percent Diff: 9.425651094436594 WING DIFFERENCES Wing Span Percent Diff: -0.02999192308385534 Wing Area Percent Diff: 33.19053282753685 HORIZONTAL TAIL DIFFERENCES HT Area Percent Diff: 45.87592829437876 VERTICAL TAIL DIFFERENCES VT Span Percent Diff: -0.664895842927617 VT Area Percent Diff: -50.62773142261092 CRUISE SEGMENT 1 DRAG DIFFERENCES Overall Cd Percent Diff: [-12.97300612] L/D Percent Diff: [19.86278453] Nacelle Cd Percent Diff: [-32.80066532] HT Cd Percent Diff: [-79.14272073] dimensionless Fuselage Cd Percent Diff: [108.78752887] VT Cd Percent Diff: [-46.05852664] dimensionless Wing Cd percent Diff: [-13.30131414] Induced Drag Cd Percent Diff: [8.17417402] CRUISE SEGMENT 1 TSFC DIFFERENCES Initial Cruise TSFC Percent Diff: [-2.16438304] FUSELAGE DIFFERENCES Weight of HB material: -29.155391997423806 Weight of VB material: 135.11625023504058 Fan Propulsive Efficiency in Cruise Segment 1 --------------------- [0.68225983]