Beginning signomial solve.
Solving took 7 GP solves and 7.75 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 2427084.18788 force_pound * meter but the right hand side evaluated to 2397885.71023 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 2.21510116729 meter but the right hand side evaluated to 1.96470271022 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 17472.5890466 newton but the right hand side evaluated to 17443.2553629 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 1242113.78791 joule / kilogram but the right hand side evaluated to 1.48132209 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 642470.56482 joule / kilogram but the right hand side evaluated to 0.643954714188 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 271789.614735 meter * newton but the right hand side evaluated to 263034.93028 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 18.5759819092 meter but the right hand side evaluated to 16.6120512333 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 10.9551734894 but the right hand side evaluated to 4.85819428352 (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 10.006928401 but the right hand side evaluated to 4.85820450308 (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 8.21525136717 but the right hand side evaluated to 4.85820456594 (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 18.6220034588 meter but the right hand side evaluated to 18.3758682447 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 18.6220034588 meter but the right hand side evaluated to 18.4513295879 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 4.67771801697 but the right hand side evaluated to 4.79404731653 (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 4.73114408179 but the right hand side evaluated to 4.81373429105 (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 7.60828629574 but the right hand side evaluated to 4.79404731653 (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 7.57971091044 but the right hand side evaluated to 4.81373429105 (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: [-6.97453055]


Total Aircraft Weight Percent Diff: [-4.95042388]


Engine Weight Percent Diff: -8.23499417305


Fuselage Weight Percent Diff: -10.9542031283


Payload Weight Percent Diff: [-0.04003557]


VT Weight Percent Diff: -24.5189573904


HT Weight Percent Diff: -85.1524935739


Wing Weight Percent Diff: 0.42608712018




WING DIFFERENCES


Wing Span Percent Diff: 0.921607203548


Wing Area Percent Diff: -6.86184095445




HORIZONTAL TAIL DIFFERENCES


HT Area Percent Diff: -54.618472857




VERTICAL TAIL DIFFERENCES




VT Span Percent Diff: -16.3231984019


VT Area Percent Diff: -29.9969796855




CRUISE SEGMENT 1 DRAG DIFFERENCES


Overall Cd Percent Diff: [-0.13088053]


Nacelle Cd Percent Diff: [ 23.80940835]


HT Cd Percent Diff: [-63.50965843] dimensionless


Fuselage Cd Percent Diff: [ 45.32349081]


VT Cd Percent Diff: [ 60.36867022] dimensionless


Induced Drag Cd Percent Diff: [ 1.0637239]


Wing Profile Cd Percent Diff: [-15.69396371]




CRUISE SEGMENT 1 TSFC DIFFERENCES


Initial Cruise TSFC Percent Diff: [ 2.99116991]




FUSELAGE DIFFERENCES


Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790004755873
Beginning signomial solve.
Solving took 7 GP solves and 9.83 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 2427098.3326 force_pound * meter but the right hand side evaluated to 2397883.45858 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 2.21510117506 meter but the right hand side evaluated to 1.96467924913 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 17472.5144496 newton but the right hand side evaluated to 17443.1796461 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 1242158.76539 joule / kilogram but the right hand side evaluated to 1.4817463524 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 642480.703391 joule / kilogram but the right hand side evaluated to 0.643968388669 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 271790.54677 meter * newton but the right hand side evaluated to 263035.227556 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 16.6121108727 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 10.9552703077 but the right hand side evaluated to 4.85819514696 (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 10.007032938 but the right hand side evaluated to 4.85820486336 (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 8.21528518871 but the right hand side evaluated to 4.85820486336 (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 18.6220588913 meter but the right hand side evaluated to 18.3759179442 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 18.6220588913 meter but the right hand side evaluated to 18.4513954173 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 4.67771675065 but the right hand side evaluated to 4.79404728819 (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 4.73115265296 but the right hand side evaluated to 4.81373841742 (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 7.60825776579 but the right hand side evaluated to 4.79404728819 (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 7.57972260007 but the right hand side evaluated to 4.81373841742 (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: [-6.97422995]


Total Aircraft Weight Percent Diff: [-4.95044675]


Engine Weight Percent Diff: -8.23560157345


Fuselage Weight Percent Diff: -10.954618425


Payload Weight Percent Diff: [-0.04052335]


VT Weight Percent Diff: -24.518327201


HT Weight Percent Diff: -85.1524351511


Wing Weight Percent Diff: 0.426467001174




WING DIFFERENCES


Wing Span Percent Diff: 0.921619801497


Wing Area Percent Diff: -6.86162729346




HORIZONTAL TAIL DIFFERENCES


HT Area Percent Diff: -54.6181566838




VERTICAL TAIL DIFFERENCES




VT Span Percent Diff: -16.3229765607


VT Area Percent Diff: -29.9965958668




CRUISE SEGMENT 1 DRAG DIFFERENCES


Overall Cd Percent Diff: [-0.13028203]


Nacelle Cd Percent Diff: [ 23.80803026]


HT Cd Percent Diff: [-63.50945817] dimensionless


Fuselage Cd Percent Diff: [ 45.32347143]


VT Cd Percent Diff: [ 60.36900645] dimensionless


Induced Drag Cd Percent Diff: [ 1.06560414]


Wing Profile Cd Percent Diff: [-15.69341222]




CRUISE SEGMENT 1 TSFC DIFFERENCES


Initial Cruise TSFC Percent Diff: [ 2.99017275]




FUSELAGE DIFFERENCES


Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790005398454
Passed

Standard Output

Standard Error
