BWB Updates

aviary/docs/user_guide_unreviewed/subsystems/blended_wing_body_FLOPS.ipynb

@@ -149,9 +149,8 @@
     "\n",
     "glue_variable(get_variable_name(Aircraft.BWB.NUM_BAYS), md_code=True)\n",
     "glue_variable(get_variable_name(Aircraft.Fuselage.SIMPLE_LAYOUT), md_code=True)\n",
-    "\n",
-    "Rear_spar_percent_chord = get_all_non_aviary_names(BWBFuselagePrelim, include_in_out='in')[0]\n",
-    "glue_variable('Rear_spar_percent_chord', Rear_spar_percent_chord, md_code=True)"
+    "glue_variable(get_variable_name(Aircraft.BWB.REAR_SPAR_PERCENT_CHORD_ROOT), md_code=True)\n",
+    "glue_variable(get_variable_name(Aircraft.BWB.REAR_SPAR_PERCENT_CHORD_CENTERLINE), md_code=True)"
    ]
   },
   {
@@ -165,7 +164,7 @@
     "\n",
     "![Fuselage size](./images/BWB_FLOPS_Fuselage_Simple_Geom.png)\n",
     "\n",
-    "Variable {glue:md}`Rear_spar_percent_chord` serves as the ratio of fuselage length and compartment length. It says that the rear spar is mounted at the side of fuselage which is 70% (default) of fuselage length from the leading edge. {glue:md}`Rear_spar_percent_chord` is hard coded for now, but can be easily converted to an Aviary variable.\n",
+    "Variable {glue:md}`Aircraft.BWB.REAR_SPAR_PERCENT_CHORD_ROOT` serves as the ratio of fuselage length and compartment length at the wing root, while variable {glue:md}`Aircraft.BWB.REAR_SPAR_PERCENT_CHORD_CENTERLINE` serves as the ratio of fuselage length and compartment length at the centeline. The default values for each of these is 0.7.\n",
     "\n",
     "The detailed layout involves more details like the number of passengers, seat pitch and seat abreast. Fuselage length and width are no longer inputs but outputs. If you have those data, it is a better choice.\n",
     "\n",
@@ -395,7 +394,8 @@
     "glue_variable(get_variable_name(Aircraft.Fuselage.CABIN_AREA), md_code=True)\n",
     "glue_variable(get_variable_name(Aircraft.Fuselage.MAX_WIDTH), md_code=True)\n",
     "glue_variable(get_variable_name(Aircraft.Fuselage.MAX_HEIGHT), md_code=True)\n",
-    "glue_variable(get_variable_name(Aircraft.Wing.ROOT_CHORD), md_code=True)"
+    "glue_variable(get_variable_name(Aircraft.Wing.ROOT_CHORD), md_code=True)\n",
+    "glue_variable(get_variable_name(Aircraft.BWB.WING_ROOT_INDEX), md_code=True)"
    ]
   },
   {
@@ -419,30 +419,55 @@
     "- {glue:md}`Aircraft.Wing.CHORD_PER_SEMISPAN_DISTRIBUTION`\n",
     "- {glue:md}`Aircraft.Wing.LOAD_PATH_SWEEP_DISTRIBUTION`\n",
     "\n",
-    "2. Suppose you have a FLOPS model with detailed wings. For example, you have:\n",
+    "2. FLOPS allows you to define the BWB detailed wing geometry from either the wing root or from the aircraft centerline. To tell FLOPS where the wing actually starts, the fueslage namelist input `NESOB` should contain the index that corresponds to the location in the detailed geometry arrays that contains the values at the wing root. This parameter is also available in Aviary as {glue:md}`Aircraft.BWB.WING_ROOT_INDEX`, though keep in mind that Aviary indexing starts at 0 instead of 1.\n",
+    "\n",
+    "3. When converting a FLOPS model, the Aviary detailed wing definition will look like the FLOPS distribution. This one starts at the centerline:\n",
     "\n",
     "```\n",
     "NETAW = 4,\n",
     "ETAW = 0.0,  .2075, .6927, 1.000,\n",
     "CHD =  48.25, 33.20, 14.19, 3.220,\n",
     "TOC =  0.125, 0.125, 0.076, 0.060,\n",
     "SWL =  0.0,   0.0,  17.0\n",
+    "\n",
+    "&FUSEIN\n",
+    "NESOB = 2\n",
     "```\n",
     "\n",
     "Note that `SWL` has one entry less than the other variables. This is because it measures the sweep angles between distribution points. The corresponding Aviary inputs should be:\n",
     "\n",
     "```\n",
-    "aircraft:wing:input_station_distribution,0.0,0.0,0.2075,0.6927,1.0,unitless\n",
-    "aircraft:wing:chord_per_semispan_distribution,-1.0,48.25,33.2,14.19,3.22,unitless\n",
-    "aircraft:wing:thickness_to_chord_distribution,-1.0,0.125,0.125,0.076,0.06,unitless\n",
-    "aircraft:wing:load_path_sweep_distribution,0.0,0.0,0.0,17.0,deg\n",
+    "aircraft:blended_wing_body_design:wing_root_index,1,unitless\n",
+    "aircraft:wing:input_station_distribution,0.0,0.2075,0.6927,1.0,unitless\n",
+    "aircraft:wing:chord_per_semispan_distribution,48.25,33.2,14.19,3.22,unitless\n",
+    "aircraft:wing:thickness_to_chord_distribution,0.125,0.125,0.076,0.06,unitless\n",
+    "aircraft:wing:load_path_sweep_distribution,0.0,0.0,17.0,deg\n",
     "```\n",
     "\n",
-    "Note that an extra entry is added with value of `0.0` or `-1.0`. These variables will be updated by Aviary when it runs. The reason for an extra entry is because FLOPS variables started the distribution of input points from wing root. For conventional aircraft, it is assumed that it is the same as starting from the centerline. But for BWB aircraft, they are different and we have to add an extra point to count for the segment from centerline to wing root. They are set to `0.0` or `-1.0` in the input file and are updated during the run.\n",
+    "Likewise, this wing definition starts at the wing root, and the Aviary inputs follow:\n",
+    "\n",
+    "```\n",
+    "NETAW = 4,\n",
+    "ETAW = .2075, .6927, 1.000,\n",
+    "CHD =  33.20, 14.19, 3.220,\n",
+    "TOC =  0.125, 0.076, 0.060,\n",
+    "SWL =  0.0,  17.0\n",
+    "\n",
+    "&FUSEIN\n",
+    "NESOB = 1\n",
+    "```\n",
+    "\n",
+    "```\n",
+    "aircraft:blended_wing_body_design:wing_root_index,0,unitless\n",
+    "aircraft:wing:input_station_distribution,0.2075,0.6927,1.0,unitless\n",
+    "aircraft:wing:chord_per_semispan_distribution,33.2,14.19,3.22,unitless\n",
+    "aircraft:wing:thickness_to_chord_distribution,0.125,0.076,0.06,unitless\n",
+    "aircraft:wing:load_path_sweep_distribution,0.0,17.0,deg\n",
+    "```\n",
     "\n",
-    "3. BWB aircraft has an non-pressurized aftbody in addition to the pressurized centerbody. Its mass {glue:md}`Aircraft.Wing.BWB_AFTBODY_MASS` is added to wing mass {glue:md}`Aircraft.Wing.MASS`.\n",
+    "4. The BWB aircraft has a non-pressurized aftbody in addition to the pressurized centerbody. Its mass {glue:md}`Aircraft.Wing.BWB_AFTBODY_MASS` is added to wing mass {glue:md}`Aircraft.Wing.MASS`.\n",
     "\n",
-    "4. In FLOPS, there are several ways to compute the cabin layout. Aviary implemented two of them. This is set by an Aviary variable {glue:md}`Aircraft.Fuselage.SIMPLE_LAYOUT`.\n",
+    "5. In FLOPS, there are several ways to compute the cabin layout. Aviary implemented two of them. This is set by an Aviary variable {glue:md}`Aircraft.Fuselage.SIMPLE_LAYOUT`.\n",
     "\n",
     "If {glue:md}`Aircraft.Fuselage.SIMPLE_LAYOUT` is true, the user should provide fuselage length as input and Aviary will compute the passenger compartment length in the case of conventional aircraft. In the case of BWB aircraft, the user should provide fuselage length, width, leading edge sweek angle and sidebody thickness to chord ratio. Aviary will conpute the passenger compartment length, wing root chord, cabin area, fuselage height, and number of bays.\n",
     "\n",
@@ -462,7 +487,7 @@
  ],
  "metadata": {
   "kernelspec": {
-   "display_name": "base",
+   "display_name": "Python 3 (ipykernel)",
    "language": "python",
    "name": "python3"
   },
@@ -476,7 +501,7 @@
    "name": "python",
    "nbconvert_exporter": "python",
    "pygments_lexer": "ipython3",
-   "version": "3.12.9"
+   "version": "3.12.3"
   }
  },
  "nbformat": 4,

aviary/models/aircraft/blended_wing_body/bwb300_baseline_FLOPS.csv

@@ -88,6 +88,7 @@ aircraft:fuel:wing_reference_capacity,0.0,lbm
 aircraft:fuel:wing_reference_capacity_term_a,0.0,unitless
 aircraft:fuel:wing_reference_capacity_term_b,0.0,unitless
 aircraft:furnishings:mass_scaler,1.118,unitless
+aircraft:fuselage:height_to_width_ratio,0.1792,unitless
 aircraft:fuselage:sidebody_thickness_to_chord,0.1792,unitless
 aircraft:fuselage:laminar_flow_lower,0.0,unitless
 aircraft:fuselage:laminar_flow_upper,0.0,unitless
@@ -142,17 +143,17 @@ aircraft:wing:airfoil_technology,2.0,unitless
 # aircraft:wing:aspect_ratio,5.4252,unitless
 # aircraft:wing:aspect_ratio_reference,0.0,unitless
 aircraft:wing:bending_material_mass_scaler,1.0,unitless
-aircraft:wing:chord_per_semispan_distribution,-1.0,48.25,33.2,18.97,14.19,10.2,3.22,unitless
+aircraft:wing:chord_per_semispan_distribution,48.25,33.2,18.97,14.19,10.2,3.22,unitless
 aircraft:wing:composite_fraction,0.85,unitless
 aircraft:wing:control_surface_area_ratio,0.3,unitless
 aircraft:wing:detailed_wing,True,unitless
 aircraft:wing:dihedral,3.0,deg
 aircraft:wing:glove_and_bat,1230.5,ft**2
-aircraft:wing:input_station_distribution,0.0,0.0,0.2075,0.415,0.6927,0.928,1.0,unitless
+aircraft:wing:input_station_distribution,0.0,0.2075,0.415,0.6927,0.928,1.0,unitless
 aircraft:wing:laminar_flow_lower,0.0,unitless
 aircraft:wing:laminar_flow_upper,0.0,unitless
 aircraft:wing:load_distribution_control,2.0,unitless
-aircraft:wing:load_path_sweep_distribution,0.0,0.0,0.0,17.0,17.0,17.0,deg
+aircraft:wing:load_path_sweep_distribution,0.0,0.0,17.0,17.0,17.0,deg
 aircraft:wing:mass_scaler,1.0,unitless
 aircraft:wing:max_camber_at_70_semispan,2.0,unitless
 aircraft:wing:misc_mass_scaler,1.0,unitless
@@ -168,7 +169,7 @@ aircraft:wing:surface_control_mass_scaler,1.0,unitless
 aircraft:wing:sweep,35.7,deg
 aircraft:wing:taper_ratio,0.311,unitless
 aircraft:wing:thickness_to_chord,0.11,unitless
-aircraft:wing:thickness_to_chord_distribution,-1.0,0.125,0.125,0.076,0.076,0.076,0.06,unitless
+aircraft:wing:thickness_to_chord_distribution,0.125,0.125,0.076,0.076,0.076,0.06,unitless
 aircraft:wing:thickness_to_chord_reference,0.0,unitless
 aircraft:wing:ultimate_load_factor,3.75,unitless
 aircraft:wing:var_sweep_mass_penalty,0.0,unitless
@@ -255,7 +256,6 @@ CONFIN.WSR,0.0
 ENGDIN.IFILL,2
 ENGDIN.MAXCR,1
 ENGDIN.NGPRT,1
-FUSEIN.TCF,0.1792
 FUSEIN.XLW,50.0
 MISSIN.ACTAB,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0
 MISSIN.ADTAB,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0

aviary/models/aircraft/blended_wing_body/bwb_detailed_FLOPS.csv

@@ -90,6 +90,7 @@ aircraft:fuel:wing_fuel_fraction,0.68835495693,unitless
 aircraft:fuel:unusable_fuel_mass_scaler,1.0,unitless
 aircraft:furnishings:mass_scaler,1.0,unitless
 aircraft:fuselage:sidebody_thickness_to_chord,0.11,unitless
+aircraft:fuselage:height_to_width_ratio,0.11,unitless
 aircraft:fuselage:mass_scaler,1.0,unitless
 aircraft:fuselage:military_cargo_floor,False,unitless
 aircraft:fuselage:num_fuselages,1,unitless
@@ -127,14 +128,14 @@ aircraft:vertical_tail:wetted_area_scaler,1.0,unitless
 aircraft:wing:aeroelastic_tailoring_factor,0.0,unitless
 aircraft:wing:airfoil_technology,2.0,unitless
 aircraft:wing:bending_material_mass_scaler,1.0,unitless
-aircraft:wing:chord_per_semispan_distribution,-1.0,58.03,0.4491,0.3884,0.3317,0.2886,0.2537,0.2269,0.2121,0.1983,0.1843,0.1704,0.1565,0.1426,0.1287,unitless
+aircraft:wing:chord_per_semispan_distribution,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,unitless
 aircraft:wing:composite_fraction,1,unitless
 aircraft:wing:control_surface_area_ratio,0.333,unitless
 aircraft:wing:detailed_wing,True,unitless
 aircraft:wing:dihedral,3.0,deg
 aircraft:wing:glove_and_bat,121.05,ft**2
-aircraft:wing:input_station_distribution,0.0,0.35,0.4,0.45,0.5,0.55,0.6,0.6499,0.7,0.75,0.8,0.85,0.8999,0.95,1,unitless
-aircraft:wing:load_path_sweep_distribution,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0,42.9,42.9,42.9,42.9,42.9,42.9,deg
+aircraft:wing:input_station_distribution,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,unitless
+aircraft:wing:load_path_sweep_distribution,0.0,0.0,0.0,0.0,0.0,0.0,0,42.9,42.9,42.9,42.9,42.9,42.9,deg
 aircraft:wing:load_distribution_control,2.0,unitless
 aircraft:wing:mass_scaler,1,unitless
 aircraft:wing:max_camber_at_70_semispan,2,unitless
@@ -151,7 +152,7 @@ aircraft:wing:sweep,35.7,deg
 aircraft:wing:taper_ratio,0.311,unitless
 aircraft:wing:thickness_to_chord,0.11,unitless
 aircraft:wing:thickness_to_chord_reference,0.11,unitless
-aircraft:wing:thickness_to_chord_distribution,-1.0,0.15,0.1132,0.0928,0.0822,0.0764,0.0742,0.0746,0.0758,0.0758,0.0756,0.0756,0.0758,0.076,0.076,unitless
+aircraft:wing:thickness_to_chord_distribution,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,unitless
 aircraft:wing:ultimate_load_factor,3.75,unitless
 aircraft:wing:var_sweep_mass_penalty,0.0,unitless
 aircraft:wing:wetted_area_scaler,1.0,unitless

aviary/models/aircraft/blended_wing_body/bwb_simple_FLOPS.csv

@@ -7,6 +7,7 @@ aircraft:anti_icing:mass_scaler,1.0,unitless
 aircraft:apu:mass_scaler,1.0,unitless
 aircraft:avionics:mass_scaler,1.0,unitless
 aircraft:blended_wing_body_design:detailed_wing_provided,False,unitless
+aircraft:blended_wing_body_design:max_bay_width,12.0,ft
 aircraft:blended_wing_body_design:passenger_leading_edge_sweep,45,deg
 aircraft:canard:area,0.0,ft**2
 aircraft:canard:aspect_ratio,0.0,unitless
@@ -135,7 +136,7 @@ aircraft:wing:control_surface_area_ratio,0.333,unitless
 aircraft:wing:detailed_wing,True,unitless
 aircraft:wing:dihedral,3.0,deg
 aircraft:wing:glove_and_bat,121.05,ft**2
-aircraft:wing:input_station_distribution,0.0,0.5,1.0,unitless
+aircraft:wing:input_station_distribution,0.5,1.0,unitless
 aircraft:wing:load_distribution_control,2.0,unitless
 aircraft:wing:mass_scaler,1,unitless
 aircraft:wing:max_camber_at_70_semispan,2,unitless

aviary/subsystems/aerodynamics/aerodynamics_builder.py

@@ -713,10 +713,22 @@ def get_parameters(self, aviary_inputs=None, user_options=None, subsystem_option
 
     def get_timeseries(self, aviary_inputs=None, user_options=None, subsystem_options=None):
         """Call get_timeseries() on all engine models and return combined result."""
-        timeseries_vars = [
-            Dynamic.Vehicle.DRAG_COEFFICIENT,
-            Dynamic.Vehicle.LIFT_COEFFICIENT,
-        ]
+        if subsystem_options is None:
+            subsystem_options = {}
+
+        timeseries_vars = []
+
+        try:
+            method = subsystem_options['method']
+        except KeyError:
+            method = None
+
+        if method != 'external':
+            timeseries_vars = [
+                Dynamic.Vehicle.DRAG_COEFFICIENT,
+                Dynamic.Vehicle.LIFT_COEFFICIENT,
+            ]
+
         return timeseries_vars
 
     def get_pre_mission_bus_variables(self, aviary_inputs=None, mission_info=None):