[Draft] FLOPS based BWB mission bench test

aviary/mission/height_energy_problem_configurator.py

@@ -394,7 +394,11 @@ def add_post_mission_systems(self, aviary_group):
             )
 
         if aviary_group.post_mission_info['include_landing']:
-            self._add_landing_systems(aviary_group)
+            if 'aircraft:wing:area' in aviary_group.aviary_inputs:
+                self._add_landing_systems(aviary_group)
+            else:
+                print('Aircraft.Wing.AREA is not given. Set include_landing = False')
+                aviary_group.post_mission_info['include_landing'] = False
 
         aviary_group.add_subsystem(
             'range_constraint',

aviary/models/aircraft/blended_wing_body/bwb_detailed_FLOPS.csv

@@ -15,7 +15,7 @@ aircraft:crew_and_payload:baggage_mass_per_passenger,44.0,lbm
 aircraft:crew_and_payload:cargo_container_mass_scaler,1.0,unitless
 aircraft:crew_and_payload:design:num_business_class,100,unitless
 aircraft:crew_and_payload:design:num_first_class,28,unitless
-aircraft:crew_and_payload:design:num_passengers,468,unitless
+# aircraft:crew_and_payload:design:num_passengers,468,unitless
 aircraft:crew_and_payload:design:num_economy_class,340,unitless
 aircraft:crew_and_payload:design:num_seats_abreast_business,4,unitless
 aircraft:crew_and_payload:design:num_seats_abreast_first,4,unitless
@@ -27,12 +27,12 @@ aircraft:crew_and_payload:design:seat_pitch_economy,32,inch
 aircraft:crew_and_payload:flight_crew_mass_scaler,1.0,unitless
 aircraft:crew_and_payload:misc_cargo,0.0,lbm
 aircraft:crew_and_payload:mass_per_passenger,165.0,lbm
-aircraft:crew_and_payload:num_business_class,100,unitless
-aircraft:crew_and_payload:num_first_class,28,unitless
 aircraft:crew_and_payload:num_flight_attendants,22,unitless
 aircraft:crew_and_payload:num_flight_crew,2,unitless
 aircraft:crew_and_payload:num_galley_crew,2,unitless
-aircraft:crew_and_payload:num_passengers,468,unitless
+aircraft:crew_and_payload:num_business_class,100,unitless
+aircraft:crew_and_payload:num_first_class,28,unitless
+# aircraft:crew_and_payload:num_passengers,468,unitless
 aircraft:crew_and_payload:num_economy_class,340,unitless
 aircraft:crew_and_payload:passenger_service_mass_scaler,1.0,unitless
 aircraft:crew_and_payload:wing_cargo,0.0,lbm
@@ -41,6 +41,12 @@ aircraft:design:empty_mass_margin_scaler,0.0,unitless
 aircraft:design:landing_to_takeoff_mass_ratio,0.8,unitless
 aircraft:design:lift_dependent_drag_coeff_factor,1.0,unitless
 aircraft:design:subsonic_drag_coeff_factor,1.0,unitless
+
+# TODO: Needed to reduce the drag so that engine wasn't full throttle in cruise.
+# There must be something about drag that still isn't working for BWB.
+aircraft:design:subsonic_drag_coeff_factor,0.7,unitless
+# aircraft:design:subsonic_drag_coeff_factor,1.0,unitless
+
 aircraft:design:supersonic_drag_coeff_factor,1.0,unitless
 aircraft:design:type,BWB,unitless
 aircraft:design:use_alt_mass,False,unitless
@@ -59,7 +65,7 @@ aircraft:engine:geopotential_alt,False,unitless
 aircraft:engine:ignore_negative_thrust,False,unitless
 aircraft:engine:interpolation_method,slinear,unitless
 aircraft:engine:mass_scaler,1,unitless
-aircraft:engine:num_engines,3,unitless
+# aircraft:engine:num_engines,3,unitless
 aircraft:engine:num_fuselage_engines,3,unitless
 aircraft:engine:num_wing_engines,0,unitless
 aircraft:engine:reference_mass,22017.0,lbm
@@ -98,8 +104,8 @@ aircraft:horizontal_tail:taper_ratio,0.0,unitless
 aircraft:horizontal_tail:thickness_to_chord,0.11,unitless
 aircraft:horizontal_tail:vertical_tail_fraction,0.0,unitless
 aircraft:horizontal_tail:wetted_area_scaler,1.0,unitless
-aircraft:hydraulics:system_pressure,3000.0,psi
 aircraft:hydraulics:mass_scaler,1.0,unitless
+aircraft:hydraulics:system_pressure,3000.0,psi
 aircraft:instruments:mass_scaler,1.0,unitless
 aircraft:landing_gear:main_gear_oleo_length,85.0,inch
 aircraft:landing_gear:main_gear_mass_scaler,1.0,unitless
@@ -152,7 +158,6 @@ aircraft:wing:var_sweep_mass_penalty,0.0,unitless
 aircraft:wing:wetted_area_scaler,1.0,unitless
 mission:constraints:max_mach,0.85,unitless
 mission:design:gross_mass,874099,lbm
-mission:design:lift_coefficient,-1.0,unitless
 mission:design:range,7750,NM
 mission:design:thrust_takeoff_per_eng,0.25,lbf
 mission:landing:initial_velocity,140,ft/s
@@ -164,6 +169,7 @@ mission:summary:fuel_flow_scaler,1.0,unitless
 settings:aerodynamics_method,FLOPS,unitless
 settings:equations_of_motion,height_energy,unitless
 settings:mass_method,FLOPS,unitless
+settings:verbosity,1,unitless
 
 # Unconverted Values
 AERIN.FLLDG,11000

aviary/models/aircraft/blended_wing_body/bwb_detailed_FLOPS.in

@@ -0,0 +1,190 @@
+468 passenger BWB - Based on Boeing BWB450-1U, Karl Geiselhart
+
+ $OPTION
+MPRINT=1,
+IOPT=1,
+IANAL=3,
+INENG=1,
+ICOST=0,
+ITAKOF=0,
+ILAND=0,
+NOPRO=0,
+NOISE=0,
+IFITE=3,
+IXFL=1,
+IPOLP=0,
+IPLTTH=0,
+ $END
+
+ $WTIN
+DGW=874099,
+VMMO=0.85,
+DIH=3,
+FLAPR=0.333,
+GLOV=121.05,
+VARSWP=0,
+FCOMP=1,
+FAERT=0,
+FSTRT=0,
+NETAW=14,
+ETAW=0.35,0.4,0.45,0.5,0.55,0.6,0.6499,0.7,0.75,0.8,0.85,0.8999,0.95,1,
+CHD=58.03,0.4491,0.3884,0.3317,0.2886,0.2537,0.2269,0.2121,0.1983,0.1843,0.1704,0.1565,0.1426,0.1287,
+TOC=0.15,0.1132,0.0928,0.0822,0.0764,0.0742,0.0746,0.0758,0.0758,0.0756,0.0756,0.0758,0.076,0.076,
+SWL=0,0,0,0,0,0,0,42.9,42.9,42.9,42.9,42.9,42.9,42.9,0,0,0,0,0,0,
+SHT=0,
+SWPHT=0,
+ARHT=0,
+TRHT=0,
+TCHT=0,
+NVERT=0,
+NFIN=2,
+SFIN=184.89,
+ARFIN=1.952,
+TRFIN=0.464,
+SWPFIN=39.42,
+TCFIN=0.08,
+NFUSE=1,
+XL=0, ! XL=137.5 for fixed geom.
+WF=0,  ! WF=64.58
+DF=0,  ! DF=17
+XLP=0,  ! XLP=40
+XMLG=85,
+XNLG=87,
+CARBAS=0,
+NEW=0,
+NEF=3,
+THRSO=86459.2,
+WENG=22017,
+EEXP=1,
+WINL=0,
+XNAC=17.433,
+DNAC=12.608,
+NPF=28,
+NPB=100,
+NPT=340,
+NSTU=22,
+NFLCR=2,
+CARGF=0,
+FRWI=1,
+FRHT=1,
+FRVT=1,
+FRFU=1,
+FRNA=0,
+WTHR=0,
+WPMSC=0,
+WHYD=1,
+WAVONC=1,
+WFURN=1,
+ISPOWE=0,
+ $END
+
+ $FUSEIN
+ACABIN=0,
+FPITCH=61,
+NFABR=4,
+BPITCH=39,
+NBABR=4,
+TPITCH=32,
+NTABR=6,
+OSSPAN=86.75,
+ $END
+ $CONFIN
+DESRNG=7750,
+OFG=1,
+OFF=0,
+GW=874099,
+AR=7.557,0,
+THRUST=70000,1,0,0,0,0,
+SW=7621.66,1,
+TR=0.311,
+SWEEP=35.7,
+TCA=0.11,
+VCMN=0.85,
+CH=39000,
+ $END
+
+ $AERIN
+MYAERO=0,
+ITPAER=2,
+CAM=2,
+AITEK=2,
+XLLAM=0,
+E=0,
+WRATIO=0.8,
+VAPPR=140,
+FLTO=11000,
+FLLDG=11000,
+THROFF=0.25,
+ $END
+
+ $ENGDIN
+IGENEN=-1,
+EIFILE='ENGDEK',
+IDLE=1,
+MAXCR=1,
+NOX=1,
+ $END
+
+ $MISSIN
+FCDO=1,
+FCDI=1,
+ISKAL=1,
+IFLAG=2,
+MSUMPT=1,
+IRW=2,
+IATA=0,
+NPCON=1,
+TAKOTM=2,
+TAXOTM=9,
+APPRTM=4,
+TAXITM=5,
+ITTFF=1,
+NCLIMB=1,
+CLAMIN=0,
+FWF=-0.001,
+NCRUSE=3,
+IOC=1,4,4,
+CRMACH=0.85,0.6,0,
+CRALT=45000,25000,1500,
+RCIN=300,
+IVS=1,
+DEAMIN=0,
+IRS=1,
+RESTRP=0.05,
+TIMMAP=2,
+ALTRAN=200,
+NCLRES=1,
+NCRRES=2,
+HOLDTM=30,
+NCRHOL=3,
+IHOPOS=1,
+THOLD=0.1,
+NCRTH=1,
+ $END
+START
+CLIMB
+CRUISE
+DESCENT
+END
+
+ $PCONIN
+CONALT=35000,
+CONMCH=0.85,
+CONPC=1,
+ICONSG=2,
+CONLIM=300,
+ICONTP=5,
+ $END
+
+ $RERUN
+ $END
+
+ $MISSIN
+IRW=1,
+NPCON=0,
+ $END
+START
+CLIMB
+CRUISE
+DESCENT
+END

aviary/models/aircraft/blended_wing_body/bwb_detailed_FLOPS_data.py

@@ -20,7 +20,6 @@
 inputs.set_val(Aircraft.Design.SUPERSONIC_DRAG_COEFF_FACTOR, 1.0)  # FCDSUP
 inputs.set_val(Aircraft.Design.ZERO_LIFT_DRAG_COEFF_FACTOR, 1.0)  # FCDO
 inputs.set_val(Aircraft.Design.TYPE, AircraftTypes.BLENDED_WING_BODY)
-inputs.set_val(Mission.Design.LIFT_COEFFICIENT, -1.0)  # FCLDES
 inputs.set_val(Aircraft.Fuselage.SIMPLE_LAYOUT, False)
 inputs.set_val(Aircraft.BWB.DETAILED_WING_PROVIDED, True)
 
@@ -50,11 +49,11 @@
 # ---------------------------
 inputs.set_val(Aircraft.CrewPayload.Design.NUM_BUSINESS_CLASS, 100)  # NPB
 inputs.set_val(Aircraft.CrewPayload.Design.NUM_FIRST_CLASS, 28)  # NPF
-inputs.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, 468, units='unitless')  # NPB+NPF+NPT
+# inputs.set_val(Aircraft.CrewPayload.Design.NUM_PASSENGERS, 468, units='unitless')  # NPB+NPF+NPT
 inputs.set_val(Aircraft.CrewPayload.Design.NUM_ECONOMY_CLASS, 340)  # NPT
 inputs.set_val(Aircraft.CrewPayload.NUM_BUSINESS_CLASS, 100)  # NPB
 inputs.set_val(Aircraft.CrewPayload.NUM_FIRST_CLASS, 28)  # NPF
-inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 468, units='unitless')  # sum of three classes
+# inputs.set_val(Aircraft.CrewPayload.NUM_PASSENGERS, 468, units='unitless')  # sum of three classes
 inputs.set_val(Aircraft.CrewPayload.NUM_ECONOMY_CLASS, 340)  # NPT
 inputs.set_val(Aircraft.CrewPayload.Design.NUM_SEATS_ABREAST_BUSINESS, 4)  # NBABR
 inputs.set_val(Aircraft.CrewPayload.Design.NUM_SEATS_ABREAST_FIRST, 4)  # NFABR
@@ -89,13 +88,13 @@
 # Fuel
 # ---------------------------
 inputs.set_val(Aircraft.Fuel.AUXILIARY_FUEL_CAPACITY, 0.0, 'lbm')  # FULAUX
-inputs.set_val(Aircraft.Fuel.DENSITY, 6.7, 'lbm/galUS')  # FULDEN
 inputs.set_val(Aircraft.Fuel.FUEL_SYSTEM_MASS_SCALER, 1.0)  # WFSYS
 inputs.set_val(Aircraft.Fuel.FUSELAGE_FUEL_CAPACITY, 0.0, 'lbm')  # FULFMX
 inputs.set_val(Aircraft.Fuel.NUM_TANKS, 7)  # NTANK
 inputs.set_val(Aircraft.Fuel.UNUSABLE_FUEL_MASS_SCALER, 1.0)  # WUF
 inputs.set_val(Aircraft.Fuel.IGNORE_FUEL_CAPACITY_CONSTRAINT, False)  # IFUFU
 inputs.set_val(Aircraft.Fuel.WING_FUEL_FRACTION, 0.68835495693, 'unitless')
+inputs.set_val(Aircraft.Fuel.DENSITY, 6.7, 'lbm/galUS')
 
 # Furnishings
 # ---------------------------
@@ -114,7 +113,7 @@
 # Horizontal Tail
 # ---------------------------
 inputs.set_val(Aircraft.HorizontalTail.AREA, 0.0, 'ft**2')  # SHT
-inputs.set_val(Aircraft.HorizontalTail.ASPECT_RATIO, 0.1)  # SHT
+inputs.set_val(Aircraft.HorizontalTail.ASPECT_RATIO, 0.1)  # ARHT
 inputs.set_val(Aircraft.HorizontalTail.TAPER_RATIO, 0.0)  # TRHT
 inputs.set_val(Aircraft.HorizontalTail.THICKNESS_TO_CHORD, 0.11)  # TCHT
 # inputs.set_val(Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION, 0.0)  # HHT
@@ -159,7 +158,7 @@
 inputs.set_val(Aircraft.Engine.REFERENCE_MASS, 22017, 'lbm')  # WENG
 inputs.set_val(Aircraft.Engine.SCALED_SLS_THRUST, 70000.0, 'lbf')  # THRUST
 inputs.set_val(Aircraft.Engine.REFERENCE_SLS_THRUST, 86459.2, 'lbf')  # THRSO
-inputs.set_val(Aircraft.Engine.NUM_ENGINES, np.array([3]))  # NEW+NEF
+# inputs.set_val(Aircraft.Engine.NUM_ENGINES, np.array([3]))  # NEW+NEF
 inputs.set_val(Aircraft.Engine.NUM_FUSELAGE_ENGINES, 3)  # NEF
 inputs.set_val(Aircraft.Engine.NUM_WING_ENGINES, np.array([0]))  # NEW
 inputs.set_val(Aircraft.Engine.THRUST_REVERSERS_MASS_SCALER, 0.0)  # WTHR