Beginning signomial solve.
Solving took 7 GP solves and 7.54 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 2427083.93694 force_pound * meter but the right hand side evaluated to 2397885.35353 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 1.96470583294 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 17472.5830259 newton but the right hand side evaluated to 17443.2501655 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 1242117.32683 joule / kilogram but the right hand side evaluated to 1.48135594274 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 642471.540859 joule / kilogram but the right hand side evaluated to 0.64395605726 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 271789.701239 meter * newton but the right hand side evaluated to 263034.880568 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 18.5759810517 meter but the right hand side evaluated to 16.6120471645 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 10.9551770492 but the right hand side evaluated to 4.85819420911 (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 10.0069398869 but the right hand side evaluated to 4.85820443238 (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 8.21525130987 but the right hand side evaluated to 4.85820448111 (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 18.6220000252 meter but the right hand side evaluated to 18.3758654437 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 18.6220000252 meter but the right hand side evaluated to 18.4513271776 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 4.6777183899 but the right hand side evaluated to 4.79404736395 (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 4.73114474585 but the right hand side evaluated to 4.8137344436 (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 7.60828528098 but the right hand side evaluated to 4.79404736395 (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 7.57971159915 but the right hand side evaluated to 4.8137344436 (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: [-6.97454158]


Total Aircraft Weight Percent Diff: [-4.95043295]


Engine Weight Percent Diff: -8.23499729354


Fuselage Weight Percent Diff: -10.9542164976


Payload Weight Percent Diff: [-0.04003559]


VT Weight Percent Diff: -24.518985894


HT Weight Percent Diff: -85.1525292456


Wing Weight Percent Diff: 0.426082456428




WING DIFFERENCES


Wing Span Percent Diff: 0.921607279772


Wing Area Percent Diff: -6.86185544756




HORIZONTAL TAIL DIFFERENCES


HT Area Percent Diff: -54.6184957332




VERTICAL TAIL DIFFERENCES




VT Span Percent Diff: -16.3232048652


VT Area Percent Diff: -29.9969905001




CRUISE SEGMENT 1 DRAG DIFFERENCES


Overall Cd Percent Diff: [-0.1308444]


Nacelle Cd Percent Diff: [ 23.80939128]


HT Cd Percent Diff: [-63.5096706] dimensionless


Fuselage Cd Percent Diff: [ 45.32349081]


VT Cd Percent Diff: [ 60.36865805] dimensionless


Induced Drag Cd Percent Diff: [ 1.06380636]


Wing Profile Cd Percent Diff: [-15.69392818]




CRUISE SEGMENT 1 TSFC DIFFERENCES


Initial Cruise TSFC Percent Diff: [ 2.99108296]




FUSELAGE DIFFERENCES


Fan Propulsive Efficiency in Cruise Segment 1
---------------------
0.790004745501
Beginning signomial solve.
Solving took 7 GP solves and 10.5 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 2427081.34298 force_pound * meter but the right hand side evaluated to 2397877.86098 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 2.21510079533 meter but the right hand side evaluated to 1.96472581258 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 17472.4999511 newton but the right hand side evaluated to 17443.1970893 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 1242107.88076 joule / kilogram but the right hand side evaluated to 1.48150781044 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 271789.7314 meter * newton but the right hand side evaluated to 263034.971207 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 16.6120278124 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 10.9552201136 but the right hand side evaluated to 4.85817571422 (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 10.007119855 but the right hand side evaluated to 4.85819028877 (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 8.21525649208 but the right hand side evaluated to 4.85819028877 (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 18.6219876237 meter but the right hand side evaluated to 18.3758628166 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 18.6219876237 meter but the right hand side evaluated to 18.4513031605 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 4.67770604652 but the right hand side evaluated to 4.79403290607 (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 4.73112281838 but the right hand side evaluated to 4.81371434879 (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 7.60820068312 but the right hand side evaluated to 4.79403290607 (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 7.57969074398 but the right hand side evaluated to 4.81371434879 (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: -8.23459215951


Fuselage Weight Percent Diff: -10.954618425


Payload Weight Percent Diff: [-0.04052335]


VT Weight Percent Diff: -24.5187046084


HT Weight Percent Diff: -85.1526281682


Wing Weight Percent Diff: 0.425462741526




WING DIFFERENCES


Wing Span Percent Diff: 0.921619801497


Wing Area Percent Diff: -6.86153415504




HORIZONTAL TAIL DIFFERENCES


HT Area Percent Diff: -54.6182928291




VERTICAL TAIL DIFFERENCES




VT Span Percent Diff: -16.3230602377


VT Area Percent Diff: -29.9968058767




CRUISE SEGMENT 1 DRAG DIFFERENCES


Overall Cd Percent Diff: [-0.12888384]


Nacelle Cd Percent Diff: [ 23.80939215]


HT Cd Percent Diff: [-63.50964062] dimensionless


Fuselage Cd Percent Diff: [ 45.32347143]


VT Cd Percent Diff: [ 60.36804424] dimensionless


Induced Drag Cd Percent Diff: [ 1.06883829]


Wing Profile Cd Percent Diff: [-15.69240054]




CRUISE SEGMENT 1 TSFC DIFFERENCES


Initial Cruise TSFC Percent Diff: [ 2.99029634]




FUSELAGE DIFFERENCES


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

Standard Output

Standard Error
