Beginning signomial solve.
Solving took 7 GP solves and 8.86 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 2427079.3929 force_pound * meter but the right hand side evaluated to 2397884.76847 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 2.21510116773 meter but the right hand side evaluated to 1.9647131073 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 17472.5810072 newton but the right hand side evaluated to 17443.2481895 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 1242117.37325 joule / kilogram but the right hand side evaluated to 1.48135566138 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 642471.582138 joule / kilogram but the right hand side evaluated to 0.643956092872 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 271789.553441 meter * newton but the right hand side evaluated to 263034.8037 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 18.5759774586 meter but the right hand side evaluated to 16.6120360521 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 10.9551738298 but the right hand side evaluated to 4.85819185495 (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 10.0069372947 but the right hand side evaluated to 4.85820207831 (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 8.21524846219 but the right hand side evaluated to 4.85820211501 (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 18.6219906945 meter but the right hand side evaluated to 18.3758570766 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 18.6219906945 meter but the right hand side evaluated to 18.4513105347 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 4.67771704584 but the right hand side evaluated to 4.79404521817 (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 4.73113737658 but the right hand side evaluated to 4.8137301389 (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 7.60828464059 but the right hand side evaluated to 4.79404521817 (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 7.579703325 but the right hand side evaluated to 4.8137301389 (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: [-6.97455052]


Total Aircraft Weight Percent Diff: [-4.95043917]


Engine Weight Percent Diff: -8.23499130092


Fuselage Weight Percent Diff: -10.9542137553


Payload Weight Percent Diff: [-0.0400356]


VT Weight Percent Diff: -24.5190594482


HT Weight Percent Diff: -85.1525485872


Wing Weight Percent Diff: 0.426060902282




WING DIFFERENCES


Wing Span Percent Diff: 0.921607342228


Wing Area Percent Diff: -6.86185506105




HORIZONTAL TAIL DIFFERENCES


HT Area Percent Diff: -54.6185228242




VERTICAL TAIL DIFFERENCES




VT Span Percent Diff: -16.3232286277


VT Area Percent Diff: -29.9970302591




CRUISE SEGMENT 1 DRAG DIFFERENCES


Overall Cd Percent Diff: [-0.13085962]


Nacelle Cd Percent Diff: [ 23.80939394]


HT Cd Percent Diff: [-63.5096966] dimensionless


Fuselage Cd Percent Diff: [ 45.32349081]


VT Cd Percent Diff: [ 60.36855825] dimensionless


Induced Drag Cd Percent Diff: [ 1.06378601]


Wing Profile Cd Percent Diff: [-15.69393449]




CRUISE SEGMENT 1 TSFC DIFFERENCES


Initial Cruise TSFC Percent Diff: [ 2.99108307]




FUSELAGE DIFFERENCES


Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790004761438
Beginning signomial solve.
Solving took 7 GP solves and 10.6 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 2427088.62423 force_pound * meter but the right hand side evaluated to 2397884.04345 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 2.21510282056 meter but the right hand side evaluated to 1.96469418074 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 17472.5174236 newton but the right hand side evaluated to 17443.2145325 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 1242107.79486 joule / kilogram but the right hand side evaluated to 1.48150632893 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 642492.385771 joule / kilogram but the right hand side evaluated to 0.643976760313 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 271790.27498 meter * newton but the right hand side evaluated to 263035.234242 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 18.575992106 meter but the right hand side evaluated to 16.6120776485 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 10.9552405589 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 10.0071294145 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 8.21526802739 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 18.6220297038 meter but the right hand side evaluated to 18.3758995683 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 18.6220297038 meter but the right hand side evaluated to 18.4513585145 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 4.67771168759 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 4.73113609971 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 7.60820580586 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 7.57970440283 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: -8.23468392487


Fuselage Weight Percent Diff: -10.954618425


Payload Weight Percent Diff: [-0.04052335]


VT Weight Percent Diff: -24.5184026826


HT Weight Percent Diff: -85.1525390837


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: -54.6182020656




VERTICAL TAIL DIFFERENCES




VT Span Percent Diff: -16.3229765607


VT Area Percent Diff: -29.9966658701




CRUISE SEGMENT 1 DRAG DIFFERENCES


Overall Cd Percent Diff: [-0.12878397]


Nacelle Cd Percent Diff: [ 23.80939215]


HT Cd Percent Diff: [-63.50953115] dimensionless


Fuselage Cd Percent Diff: [ 45.32347143]


VT Cd Percent Diff: [ 60.36868571] dimensionless


Induced Drag Cd Percent Diff: [ 1.06873722]


Wing Profile Cd Percent Diff: [-15.69240054]




CRUISE SEGMENT 1 TSFC DIFFERENCES


Initial Cruise TSFC Percent Diff: [ 2.99030664]




FUSELAGE DIFFERENCES


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

Standard Output

Standard Error
