Beginning signomial solve.
Solving took 7 GP solves and 7.9 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 2427081.03018 force_pound * meter but the right hand side evaluated to 2397885.24809 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 2.21510116755 meter but the right hand side evaluated to 1.96470763423 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 17472.5830485 newton but the right hand side evaluated to 17443.2501635 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 1242117.40097 joule / kilogram but the right hand side evaluated to 1.48135579038 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 642471.493898 joule / kilogram but the right hand side evaluated to 0.643956007564 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 271789.72475 meter * newton but the right hand side evaluated to 263034.871604 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 18.5759804037 meter but the right hand side evaluated to 16.6120447728 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 10.9551760799 but the right hand side evaluated to 4.85819328394 (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 10.0069385064 but the right hand side evaluated to 4.85820350818 (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 8.21525042921 but the right hand side evaluated to 4.8582035575 (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 18.6219981448 meter but the right hand side evaluated to 18.3758638627 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 18.6219981448 meter but the right hand side evaluated to 18.4513195483 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 4.67771774199 but the right hand side evaluated to 4.79404652853 (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 4.73113974649 but the right hand side evaluated to 4.81373202851 (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 7.60828509817 but the right hand side evaluated to 4.79404652853 (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 7.5797058414 but the right hand side evaluated to 4.81373202851 (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: [-6.97454056]


Total Aircraft Weight Percent Diff: [-4.95043323]


Engine Weight Percent Diff: -8.23499476465


Fuselage Weight Percent Diff: -10.9542143867


Payload Weight Percent Diff: [-0.04003559]


VT Weight Percent Diff: -24.5189947229


HT Weight Percent Diff: -85.1525271489


Wing Weight Percent Diff: 0.426073197097




WING DIFFERENCES


Wing Span Percent Diff: 0.921607276685


Wing Area Percent Diff: -6.86184728835




HORIZONTAL TAIL DIFFERENCES


HT Area Percent Diff: -54.6184941987




VERTICAL TAIL DIFFERENCES




VT Span Percent Diff: -16.3232082975


VT Area Percent Diff: -29.9969962429




CRUISE SEGMENT 1 DRAG DIFFERENCES


Overall Cd Percent Diff: [-0.13085656]


Nacelle Cd Percent Diff: [ 23.80938392]


HT Cd Percent Diff: [-63.50967264] dimensionless


Fuselage Cd Percent Diff: [ 45.32349081]


VT Cd Percent Diff: [ 60.3686303] dimensionless


Induced Drag Cd Percent Diff: [ 1.06378923]


Wing Profile Cd Percent Diff: [-15.69393727]




CRUISE SEGMENT 1 TSFC DIFFERENCES


Initial Cruise TSFC Percent Diff: [ 2.99108427]




FUSELAGE DIFFERENCES


Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790004744807
Beginning signomial solve.
Solving took 7 GP solves and 13.4 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 2427086.19714 force_pound * meter but the right hand side evaluated to 2397882.46207 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 2.21510136492 meter but the right hand side evaluated to 1.96471500661 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 17472.4547829 newton but the right hand side evaluated to 17443.1447597 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 1242169.52199 joule / kilogram but the right hand side evaluated to 1.48194195583 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 642492.747192 joule / kilogram but the right hand side evaluated to 0.643983200112 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 271790.00319 meter * newton but the right hand side evaluated to 263035.220871 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 18.576010682 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 10.9552280504 but the right hand side evaluated to 4.85819028877 (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 10.0071558568 but the right hand side evaluated to 4.85820000516 (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 8.21524854222 but the right hand side evaluated to 4.85820000516 (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 18.622017235 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 18.622017235 meter but the right hand side evaluated to 18.4513400632 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 4.67771559461 but the right hand side evaluated to 4.79404249415 (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 4.73113628213 but the right hand side evaluated to 4.81372878996 (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 7.60819310639 but the right hand side evaluated to 4.79404249415 (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 7.57970348661 but the right hand side evaluated to 4.81372878996 (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: -8.23523451512


Fuselage Weight Percent Diff: -10.954618425


Payload Weight Percent Diff: [-0.04052335]


VT Weight Percent Diff: -24.5187046084


HT Weight Percent Diff: -85.1526875576


Wing Weight Percent Diff: 0.426467001174




WING DIFFERENCES


Wing Span Percent Diff: 0.921619801497


Wing Area Percent Diff: -6.86172043179




HORIZONTAL TAIL DIFFERENCES


HT Area Percent Diff: -54.6183382108




VERTICAL TAIL DIFFERENCES




VT Span Percent Diff: -16.3230602377


VT Area Percent Diff: -29.9968058767




CRUISE SEGMENT 1 DRAG DIFFERENCES


Overall Cd Percent Diff: [-0.12838448]


Nacelle Cd Percent Diff: [ 23.80902073]


HT Cd Percent Diff: [-63.50960413] dimensionless


Fuselage Cd Percent Diff: [ 45.32347143]


VT Cd Percent Diff: [ 60.36836498] dimensionless


Induced Drag Cd Percent Diff: [ 1.06974791]


Wing Profile Cd Percent Diff: [-15.691979]




CRUISE SEGMENT 1 TSFC DIFFERENCES


Initial Cruise TSFC Percent Diff: [ 2.98961661]




FUSELAGE DIFFERENCES


Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790003486651
Passed

Standard Output

Standard Error
