Note: Please follow the instructions from the Overview page to install MDO Agent Deck before using the wing agent.
What the Wing Agent Does
The wing agent supports these skills:
generate-cfd-mesh: build the wing CFD mesh and mesh-quality outputs.generate-fea-mesh: build the wingbox FEA mesh for an existing wing CFD mesh.generate-aero-struct-mesh: build both the CFD mesh and the wingbox FEA mesh in one case; this is the prerequisite for the aero-structural skills.run-cfd-simulation: run steady aerodynamic CFD from an existing wing mesh.run-aero-optimization: run single-point or multipoint aerodynamic shape optimization for the wing.run-aero-struct-simulation: run coupled aero-structural analysis.run-aero-struct-optimization: run coupled aero-structural optimization (drag or wingbox-mass objective, single or multiple load factors).
Standard Inputs
airfoil_profiles(list[str], default: [“naca0012”, “naca0012”]): N sectional airfoil profile names ordered wing root to tip.chords(list[float], default: [1.0, 1.0]): N sectional chord lengths in meters ordered wing root to tip.spans(list[float], default: [3.0]): N-1 sectional HALF-WING SPAN lengths in meters, one per span segment ordered wing root to tip.sweeps(list[float], default: [0.0]): N-1 sectional leading-edge sweep angles in degrees, one per span segment ordered wing root to tip.dihedrals(list[float], default: [0.0]): N-1 sectional dihedral angles in degrees, one per span segment ordered wing root to tip.twists(list[float], default: [0.0]): N-1 sectional twist angles in degrees, one per span segment ordered wing root to tip. Positive is nose-up.mesh_cells(int, default: 200000): target total volume mesh cell count for the wing.y_plus(float, default: 50.0): target near-wall mesh spacing (y+oryPlus) for the wing mesh generation.mach_number(float, default: 0.2): reference Mach number (Ma) for wing mesh generation.reynolds_number(float, default: 5e6): reference Reynolds number for wing mesh generation when altitude is null; with altitude, mesh sizing calculates it after generating the wing geometry.altitude(float, default: None): optional standard-atmosphere altitude in meters (0 to 20000). When set, the configured OpenVSP wing MAC determines the CFD Reynolds number after geometry generation.local_refine_box(list[list[float]], default: None): optional two-corner local refinement box[[x0, y0, z0], [x1, y1, z1]]. Leave unset for no local refinement.
n_ribs(int, default: 10): number of ribs in the spanwise direction.n_spars(int, default: 2): number of spars in the chordwise direction.total_elements_target(int, default: 3000): requested total number of shell elements for the wingbox mesh.wingbox_span(float, default: 0.95): fraction of the modeled HALF-WING SPAN covered by the wingbox layout. Default: 0.95.wingbox_chord_start(float, default: 0.2): wingbox front spar position as a fraction of local chord.wingbox_chord_end(float, default: 0.8): wingbox rear spar position as a fraction of local chord.
airfoil_profiles(list[str], default: [“naca0012”, “naca0012”]): N sectional airfoil profile names ordered wing root to tip.chords(list[float], default: [1.0, 1.0]): N sectional chord lengths in meters ordered wing root to tip.spans(list[float], default: [3.0]): N-1 sectional HALF-WING SPAN lengths in meters, one per span segment ordered wing root to tip.sweeps(list[float], default: [0.0]): N-1 sectional leading-edge sweep angles in degrees, one per span segment ordered wing root to tip.dihedrals(list[float], default: [0.0]): N-1 sectional dihedral angles in degrees, one per span segment ordered wing root to tip.twists(list[float], default: [0.0]): N-1 sectional twist angles in degrees, one per span segment ordered wing root to tip. Positive is nose-up.mesh_cells(int, default: 200000): target total volume mesh cell count for the wing.y_plus(float, default: 50.0): target near-wall mesh spacing (y+oryPlus) for the wing mesh generation.mach_number(float, default: 0.2): reference Mach number (Ma) for wing mesh generation.reynolds_number(float, default: 5e6): reference Reynolds number for wing mesh generation when altitude is null; with altitude, mesh sizing calculates it after generating the wing geometry.altitude(float, default: None): optional standard-atmosphere altitude in meters (0 to 20000). When set, the configured OpenVSP wing MAC determines the CFD Reynolds number after geometry generation.local_refine_box(list[list[float]], default: None): optional two-corner local refinement box[[x0, y0, z0], [x1, y1, z1]]. Leave unset for no local refinement.n_ribs(int, default: 10): number of ribs in the spanwise direction.n_spars(int, default: 2): number of spars in the chordwise direction.total_elements_target(int, default: 3000): requested total number of shell elements for the wingbox mesh.wingbox_span(float, default: 0.95): fraction of the modeled HALF-WING SPAN covered by the wingbox layout. Default: 0.95.wingbox_chord_start(float, default: 0.2): wingbox front spar position as a fraction of local chord.wingbox_chord_end(float, default: 0.8): wingbox rear spar position as a fraction of local chord.
angle_of_attack(float, default: 2.0): freestream angle of attack (AoA) in degrees.fixed_lift_coeff(float, default: -1.0): automatically vary the angle of attack to compute drag at the prescribed lift coefficient. Set it to -1.0 to disable.airfoil_profiles(list[str], default: inherited from generate-cfd-mesh): section airfoil profile names inherited from generate-cfd-mesh.mach_number(float, default: inherited from generate-cfd-mesh): reference Mach number. Inherited from generate-cfd-mesh if not provided.reynolds_number(float, default: inherited from generate-cfd-mesh): reference Reynolds number. Inherited from generate-cfd-mesh if not provided.altitude(float, default: inherited from generate-cfd-mesh): optional standard-atmosphere altitude in meters inherited from the mesh; when set, Reynolds uses the wing reference length and overrides a supplied value.chords(list[float], default: inherited from generate-cfd-mesh): section chord lengths inherited from generate-cfd-mesh.sweeps(list[float], default: inherited from generate-cfd-mesh): section leading-edge sweep angles inherited from generate-cfd-mesh.dihedrals(list[float], default: inherited from generate-cfd-mesh): section dihedral angles inherited from generate-cfd-mesh.spans(list[float], default: inherited from generate-cfd-mesh): sectional HALF-WING SPAN lengths in meters inherited from generate-cfd-mesh.twists(list[float], default: inherited from generate-cfd-mesh): section twist angles inherited from generate-cfd-mesh.n_cpu_cores(int, default: 1): number of CPU cores (MPI ranks) to use.
angle_of_attack(float, default: 2.0): initial freestream angle of attack (AoA) in degrees.airfoil_profiles(list[str], default: inherited from generate-cfd-mesh): section airfoil profile names inherited from generate-cfd-mesh.mach_number(float, default: inherited from generate-cfd-mesh): freestream Mach number. Inherited from generate-cfd-mesh if not provided.reynolds_number(float, default: inherited from generate-cfd-mesh): freestream Reynolds number. Inherited from generate-cfd-mesh if not provided.altitude(float, default: inherited from generate-cfd-mesh): optional standard-atmosphere altitude in meters inherited from the mesh; when set, Reynolds uses the wing reference length and overrides a supplied value.optimizer(str, default: “Uno”): optimization algorithm to use. Options are Uno (default), SLSQP, SNOPT, and EGO. The number of CST coefficients per airfoil surface is set by the advanced parameterprofile_fit_coeff_count(default 6).lift_constraint(list[float], default: [0.5]): target lift coefficient lower bound for each optimization point. Supply more than one entry for multipoint optimization; its length must equalmultipoint_weight.multipoint_weight(list[float], default: [1.0]): objective weight for each optimization point. Provide one entry perlift_constraintvalue; weights must sum to 1.0.active_design_vars(list[str], default: [“cst_coeffs”, “twists”]): design variable groups the optimizer may change. Supported values: cst_coeffs, twists, spans, sweeps, dihedrals, chords (section tip chords), wing_root_chord.le_radius_constraint(float, default: 0.7): lower bound on leading-edge radius constraint; normalized wrt the baseline radius (1.0). Set to a negative value to disable it.thickness_constraint(float, default: 0.5): lower bound on airfoil thickness constraint; normalized wrt the baseline thickness (1.0). Set to a negative value to disable it.camber_curvature_constraint(int, default: 0): camber-line smoothness constraint that prevents wavy optimized airfoil shapes. 1 to enable, 0 to disable (default).volume_constraint(float, default: 1.0): lower bound on airfoil volume constraint; normalized wrt the baseline volume (1.0). Set to a negative value to disable it.area_constraint(float, default: -1.0): upper bound on wing planform area constraint; normalized wrt the baseline area (1.0). Set to a negative value to disable it.same_profile_constraint(int, default: 0): set to 1 to keep the airfoil profile (CST coefficients) of every wing section identical via linear equality constraints; applies only when cst_coeffs is active. Use 0 to disable it.max_opt_iters(int, default: 50): maximum number of optimization iterations.n_ego_doe_pts(int, default: 20): number of initial design of experiment (DOE) sample points used by the EGO optimizer.chords(list[float], default: inherited from generate-cfd-mesh): section chord lengths inherited from generate-cfd-mesh.sweeps(list[float], default: inherited from generate-cfd-mesh): section leading-edge sweep angles inherited from generate-cfd-mesh.dihedrals(list[float], default: inherited from generate-cfd-mesh): section dihedral angles inherited from generate-cfd-mesh.spans(list[float], default: inherited from generate-cfd-mesh): sectional HALF-WING SPAN lengths in meters inherited from generate-cfd-mesh.twists(list[float], default: inherited from generate-cfd-mesh): section twist angles inherited from generate-cfd-mesh.n_cpu_cores(int, default: 1): number of CPU cores (MPI ranks) to use.
angle_of_attack(float, default: 3.0): freestream angle of attack (AoA) in degrees.fixed_force(int, default: 0): automatically vary the angle of attack to compute drag at the force balance lift=weight. 0: disable. 1: enableairfoil_profiles(list[str], default: inherited from generate-aero-struct-mesh): section airfoil profile names inherited from generate-aero-struct-mesh.mach_number(float, default: inherited from generate-aero-struct-mesh): freestream Mach number inherited from generate-aero-struct-mesh when omitted.reynolds_number(float, default: inherited from generate-aero-struct-mesh): freestream Reynolds number inherited from generate-aero-struct-mesh when omitted.altitude(float, default: inherited from generate-aero-struct-mesh): optional standard-atmosphere altitude in meters inherited from the mesh; when set, Reynolds uses the wing reference length and overrides a supplied value.ref_half_mass(float, default: 10000.0): reference half-aircraft mass in kg, excluding the modeled half-wingbox mass.struct_panel_thickness(float, default: 0.01): initial structural shell thickness in meters.stiffener_pitch(float, default: 0.2): stiffener spacing in meters, transverse to the stiffeners (default 0.2 m).stiffener_height(float, default: 0.02): initial stiffener height in meters (default 0.02 m).stiffener_thickness(float, default: 0.005): initial stiffener thickness in meters (default 5 mm).stiffener_flange_fraction(float, default: 1.0): dimensionless ratio of stiffener flange width to stiffener height.struct_safety_factor(float, default: 1.5): safety factor used for the structural failure constraint.le_radius_constraint(float, default: 0.7): lower bound on leading-edge radius constraint; normalized wrt the baseline radius (1.0). Set to a negative value to disable it.thickness_constraint(float, default: 0.5): lower bound on airfoil thickness constraint; normalized wrt the baseline thickness (1.0). Set to a negative value to disable it.volume_constraint(float, default: 1.0): lower bound on airfoil volume constraint; normalized wrt the baseline volume (1.0). Set to a negative value to disable it.area_constraint(float, default: -1.0): upper bound on wing planform area constraint; normalized wrt the baseline area (1.0). Set to a negative value to disable it.chords(list[float], default: inherited from generate-aero-struct-mesh): section chord lengths inherited from generate-aero-struct-mesh.sweeps(list[float], default: inherited from generate-aero-struct-mesh): section leading-edge sweep angles inherited from generate-aero-struct-mesh.dihedrals(list[float], default: inherited from generate-aero-struct-mesh): section dihedral angles inherited from generate-aero-struct-mesh.spans(list[float], default: inherited from generate-aero-struct-mesh): sectional HALF-WING SPAN lengths in meters inherited from generate-aero-struct-mesh.twists(list[float], default: inherited from generate-aero-struct-mesh): section twist angles inherited from generate-aero-struct-mesh.n_cpu_cores(int, default: 1): number of CPU cores (MPI ranks) to use.
optimizer(str, default: “Uno”): optimization algorithm to use. Options are Uno (default), SLSQP, SNOPT, and EGO. EGO requires a non-emptystruct_dv_interp_eta.objective(list[str], default: [“drag”]): objective function for eachload_factorpoint:drag(wing CD) ormass(wingbox mass); its length must equalload_factor.n_ego_doe_pts(int, default: 20): number of initial design of experiment (DOE) sample points used by the EGO optimizer.struct_dv_interp_eta(list[float], default: []): piecewise-linearly interpolated structural DVs (panels and stiffeners). Set to [0, 1] to interpolate from root to tip, and add intermediate span fractions (e.g. [0, 0.3, 1]) if needed. Empty (default) keeps independent DVs for every panel. EGO requires a non-empty value.angle_of_attack(float, default: 3.0): initial freestream angle of attack (AoA) in degrees.load_factor(list[float], default: [1.0]): wing load factor for each optimization point. Supply more than one entry for multipoint optimization; its length must equalmultipoint_weight.multipoint_weight(list[float], default: [1.0]): objective weight for each optimization point. Provide one entry perload_factorvalue; weights must sum to 1.0.airfoil_profiles(list[str], default: inherited from generate-aero-struct-mesh): section airfoil profile names inherited from generate-aero-struct-mesh.mach_number(float, default: inherited from generate-aero-struct-mesh): freestream Mach number inherited from generate-aero-struct-mesh when omitted.reynolds_number(float, default: inherited from generate-aero-struct-mesh): freestream Reynolds number inherited from generate-aero-struct-mesh when omitted.altitude(float, default: inherited from generate-aero-struct-mesh): optional standard-atmosphere altitude in meters inherited from the mesh; when set, Reynolds uses the wing reference length and overrides a supplied value.max_opt_iters(int, default: 100): maximum number of optimization iterations.ref_half_mass(float, default: 10000.0): reference half-aircraft mass in kg, excluding the modeled half-wingbox mass.struct_panel_thickness(float, default: 0.003): initial structural shell thickness in meters.stiffener_pitch(float, default: 0.2): stiffener spacing in meters, transverse to the stiffeners (default 0.2 m).stiffener_height(float, default: 0.02): initial stiffener height in meters (default 0.02 m).stiffener_thickness(float, default: 0.005): initial stiffener thickness in meters (default 5 mm).stiffener_flange_fraction(float, default: 1.0): dimensionless ratio of stiffener flange width to stiffener height.struct_safety_factor(float, default: 1.5): safety factor used for the structural failure constraint.active_design_vars(list[str], default: [“cst_coeffs”, “twists”]): wing shape design variable groups the optimizer may change. Supported values: cst_coeffs, twists, spans, sweeps, dihedrals, chords (section tip chords), wing_root_chord.le_radius_constraint(float, default: 0.7): lower bound on leading-edge radius constraint; normalized wrt the baseline radius (1.0). Set to a negative value to disable it.thickness_constraint(float, default: 0.5): lower bound on airfoil thickness constraint; normalized wrt the baseline thickness (1.0). Set to a negative value to disable it.camber_curvature_constraint(int, default: 0): camber-line smoothness constraint that prevents wavy optimized airfoil shapes. 1 to enable, 0 to disable (default).volume_constraint(float, default: 1.0): lower bound on airfoil volume constraint; normalized wrt the baseline volume (1.0). Set to a negative value to disable it.area_constraint(float, default: -1.0): upper bound on wing planform area constraint; normalized wrt the baseline area (1.0). Set to a negative value to disable it.chords(list[float], default: inherited from generate-aero-struct-mesh): section chord lengths inherited from generate-aero-struct-mesh.sweeps(list[float], default: inherited from generate-aero-struct-mesh): section leading-edge sweep angles inherited from generate-aero-struct-mesh.dihedrals(list[float], default: inherited from generate-aero-struct-mesh): section dihedral angles inherited from generate-aero-struct-mesh.spans(list[float], default: inherited from generate-aero-struct-mesh): sectional HALF-WING SPAN lengths in meters inherited from generate-aero-struct-mesh.twists(list[float], default: inherited from generate-aero-struct-mesh): section twist angles inherited from generate-aero-struct-mesh.n_cpu_cores(int, default: 1): number of CPU cores (MPI ranks) to use.
Advanced Parameters
camera_scale(float, default: 1.0): camera zoom multiplier for the 3D mesh and flow-field plots. Values below 1.0 zoom in, values above 1.0 zoom out; 1.0 is the default framing.farfield_scale(float, default: 20.0): outer-boundary distance scale used to compute the volume-mesh march distance asfarfield_scale * root_chord.neighbor_rings(int, default: null): neighbor-ring depth used by the diffusion mesh extrusion smoother. Leave null to auto-scale with total mesh cells; set an int to override.pressure_profile_fractions(list[float], default: [0.1, 0.5, 0.9]): spanwise fractions used for wing pressure-profile plots, for example[0.2, 0.4, 0.8].blunt_te(float, default: 0.01): trailing-edge bluntness as a fraction of chord.surf_mesh_cells(int, default: null): surface tessellation cell count used for wing.xyz generation density. Set together with n_layers to override mesh_cells-based auto sizing.n_layers(int, default: null): number of extrusion layers for the volume mesh. Set together with surf_mesh_cells to override mesh_cells-based auto sizing.trailing_edge_shape(str, default: “rounded”): trailing-edge cap style for OpenVSP. Userounded(default) orflat.tip_cluster(float, default: 0.1): spanwise clustering factor at the tip, where 0 is dense and 1 is uniform.le_cluster(float, default: 0.1): chordwise clustering factor at the leading edge, where 0 is dense and 1 is uniform.te_cluster(float, default: 0.1): chordwise clustering factor at the trailing edge, where 0 is dense and 1 is uniform.d0(float, default: -1.0): first-layer height in meters. Use a negative value to let the wrapper usey_plus,mach_number, andreynolds_numberinstead.diffusion_sweeps(int, default: 10): number of smoothing sweeps per layer for diffusion mesh extrusion.diffuse_start(float, default: null): smoothing onset distance in meters. If null, mesh wrapper default behavior is used.sym_axis(str, default: “y”): symmetry plane axis passed to the volume mesh generator.sym_decay(float, default: -1.0): symmetry damping decay length. Use a negative value to let mdo_agent_mesh compute it automatically.max_nonorthogonality_thresholds(list[float], default: [70.0, 80.0]): [Pass, Warning] thresholds for maximum non-orthogonality.max_aspect_ratio_thresholds(list[float], default: [1000.0, 10000.0]): [Pass, Warning] thresholds for maximum aspect ratio.max_skewness_thresholds(list[float], default: [4.0, 6.0]): [Pass, Warning] thresholds for maximum skewness.
camera_scale(float, default: 1.0): camera zoom multiplier for the 3D mesh and flow-field plots. Values below 1.0 zoom in, values above 1.0 zoom out; 1.0 is the default framing.
- Same advanced parameters as
generate-cfd-mesh.
camera_scale(float, default: 1.0): camera zoom multiplier for the 3D mesh and flow-field plots. Values below 1.0 zoom in, values above 1.0 zoom out; 1.0 is the default framing.cst_coeffs(list[float], default: null): user-supplied wing CST coefficients, ordered section by section as[upper..., lower...].len(cst_coeffs)must equal2 * profile_fit_coeff_count * number_of_sections. Set this only to parameterize the wing sections with explicit numeric CST values; leave it null (default) to use the named profiles inairfoil_profiles.cp_plot_bounds(list[float], default: [-2.0, 2.0]): [Lower, upper] bounds of the Cp axis and colorbar shared by the pressure-profile and Cp flow-field plots.plot_tail_fraction(float, default: 1.0): fraction of the CD/CL/CM history to plot from the end. 1.0 plots the full history; 0.2 plots the final 20 percent.force_std_thresholds(list[float], default: [0.0001, 0.05]): [Pass, Warning] thresholds for raw force-coefficient standard deviation.initialize_from(str, default: null): warm-start source case name. When set, the field staged into 0/ is kept instead of resetting to the uniform freestream.max_flow_iters(int, default: 10000): maximum number of flow iterations written to the case controlDict endTime/writeInterval settings.pressure_profile_fractions(list[float], default: [0.1, 0.5, 0.9]): spanwise fractions used for wing pressure-profile plots, for example[0.2, 0.4, 0.8].primal_func_slope_tol(float, default: 1e-6): DAFoam primal function slope tolerance passed to script_run_dafoam.py.primal_func_std_tol(float, default: 0.04): DAFoam primal function standard deviation tolerance passed to script_run_dafoam.py.profile_fit_coeff_count(int, default: 6): number of coefficients used to fit each airfoil surface. For example,4fits 4 coefficients for the upper surface and 4 for the lower surface.solver_name(str, default: null): explicit solver override. Supported values areDASimpleFoam(incompressible),DARhoSimpleFoam(compressible),DARhoSimpleCFoam(compressible/transonic), andDAHisaFoam(compressible/transonic/supersonic). Leave unset,null, ornoneto use the default Mach-based selection.transonic_mach_boundary(float, default: 0.4): transonic Mach split used by the default solver selection whensolver_nameis not set.turbulence_model(str, default: “SpalartAllmaras”): OpenFOAM RANS turbulence model. Supported values areSpalartAllmaras(SA) andkOmegaSST(SST).u_plot_bounds(list[float], default: [-1.0, 1.0]): [Lower, upper] bounds of the normalized velocity colorbar for the U flow-field plot.residual_drop_orders_thresholds(list[float], default: [6.0, 3.0]): [Pass, Warning] thresholds for minimum residual drop in log10 orders.
adjoint_residual_drop_orders_thresholds(list[float], default: [5.0, 3.0]): [Pass, Warning] thresholds for minimum adjoint residual drop in log10 orders.camera_scale(float, default: 1.0): camera zoom multiplier for the 3D mesh and flow-field plots. Values below 1.0 zoom in, values above 1.0 zoom out; 1.0 is the default framing.cst_coeffs(list[float], default: null): user-supplied wing CST coefficients, ordered section by section as[upper..., lower...].len(cst_coeffs)must equal2 * profile_fit_coeff_count * number_of_sections. Set this only to parameterize the wing sections with explicit numeric CST values; leave it null (default) to use the named profiles inairfoil_profiles.cp_plot_bounds(list[float], default: [-2.0, 2.0]): [Lower, upper] bounds of the Cp axis and colorbar shared by the pressure-profile and Cp flow-field plots.dv_bounds(dict[str, list[float]], default: {“CSTCoeffs”: [-0.4, 0.4], “Twist”: [-5.0, 5.0], “Sweep”: [-15.0, 15.0], “Dihedral”: [0.0, 5.0], “AoA”: [0.0, 10.0], “Span”: [0.5, 1.5], “Chord”: [0.5, 1.5], “Wing_Root_Chord”: [1.0, 1.0]}): design-variable lower/upper bounds shared by EGO and regular optimization. All keys are required. Span, Chord (section tip chords), and Wing_Root_Chord (root chord of the whole wing) are multipliers of the baseline value, e.g. [0.9, 1.1] is +-10%; all other keys are absolute values (degrees for Twist, Sweep, Dihedral, AoA). Wing_Root_Chord defaults to be fixed with bounds [1.0, 1.0].final_feasibility_thresholds(list[float], default: [0.0001, 0.01]): [Pass, Warning] thresholds for final feasibility.flow_residual_drop_orders_thresholds(list[float], default: [6.0, 3.0]): [Pass, Warning] thresholds for minimum flow residual drop in log10 orders.max_adj_iters(int, default: 1000): maximum GMRES iterations used by the DAFoam adjoint linear solve.max_flow_iters(int, default: 10000): maximum number of flow iterations written to the case controlDict endTime/writeInterval settings.objective_reduction_pct_thresholds(list[float], default: [5.0, 1.0]): [Pass, Warning] thresholds for objective reduction in percent.pc_fill_level(int, default: 1): ILU fill level used by the DAFoam adjoint preconditioner.pressure_profile_fractions(list[float], default: [0.1, 0.5, 0.9]): spanwise fractions used for wing pressure-profile plots, for example[0.2, 0.4, 0.8].primal_func_slope_tol(float, default: 1e-6): DAFoam primal function slope tolerance passed to script_run_dafoam.py.primal_func_std_tol(float, default: 0.04): DAFoam primal function standard deviation tolerance passed to script_run_dafoam.py.profile_fit_coeff_count(int, default: 6): number of coefficients used to fit each airfoil surface. For example,4fits 4 coefficients for the upper surface and 4 for the lower surface.solver_name(str, default: null): explicit solver override. Supported values areDASimpleFoam(incompressible),DARhoSimpleFoam(compressible),DARhoSimpleCFoam(compressible/transonic), andDAHisaFoam(compressible/transonic/supersonic). Leave unset,null, ornoneto use the default Mach-based selection.transonic_mach_boundary(float, default: 0.4): transonic Mach split used by the default solver selection whensolver_nameis not set.turbulence_model(str, default: “SpalartAllmaras”): OpenFOAM RANS turbulence model. Supported values areSpalartAllmaras(SA) andkOmegaSST(SST).u_plot_bounds(list[float], default: [-1.0, 1.0]): [Lower, upper] bounds of the normalized velocity colorbar for the U flow-field plot.n_multi_start(int, default: 20): number of multi-start points for the EGO internal EI optimization.ei_tol(float, default: 0.0001): EGO internal expected improvement (EI) optimization tolerance.ego_seed(int, default: 0): random seed used by the EGO optimizer DOE and infill sampling.ego_tol(float, default: 0.001): objective variation tolerance for the EGO optimization.ego_cstr_tol(float, default: 0.001): constraint tolerance used by EGO and its lift-trim searches.
camera_scale(float, default: 1.0): camera zoom multiplier for the 3D mesh and flow-field plots. Values below 1.0 zoom in, values above 1.0 zoom out; 1.0 is the default framing.cst_coeffs(list[float], default: null): user-supplied wing CST coefficients, ordered section by section as[upper..., lower...].len(cst_coeffs)must equal2 * profile_fit_coeff_count * number_of_sections. Set this only to parameterize the wing sections with explicit numeric CST values; leave it null (default) to use the named profiles inairfoil_profiles.cp_plot_bounds(list[float], default: [-2.0, 2.0]): [Lower, upper] bounds of the Cp axis and colorbar shared by the pressure-profile and Cp flow-field plots.force_std_thresholds(list[float], default: [0.0001, 0.05]): [Pass, Warning] thresholds for raw force-coefficient standard deviation.initialize_from(str, default: null): warm-start source case name. When set, the field staged into 0/ is kept instead of resetting to the uniform freestream.nlbgs_abs_tol(float, default: 2.0): absolute tolerance for the aerostructural OpenMDAONonlinearBlockGSnonlinear block Gauss-Seidel solver.nlbgs_rel_tol(float, default: 1e-7): relative tolerance for the aerostructural OpenMDAONonlinearBlockGSnonlinear block Gauss-Seidel solver.pressure_profile_fractions(list[float], default: [0.1, 0.5, 0.9]): spanwise fractions used for wing pressure-profile plots, for example[0.2, 0.4, 0.8].primal_func_slope_tol(float, default: 0.0001): DAFoam primal function slope tolerance passed to script_run_dafoam.py.primal_func_std_tol(float, default: 0.05): DAFoam primal function standard deviation tolerance passed to script_run_dafoam.py.primal_min_iters(int, default: 100): minimum number of primal iterations. This also sets thenStepswindow used by the primal function standard deviation convergence check.profile_fit_coeff_count(int, default: 6): number of coefficients used to fit each airfoil surface. For example,4fits 4 coefficients for the upper surface and 4 for the lower surface.solver_name(str, default: null): explicit solver override. Supported values areDASimpleFoam(incompressible),DARhoSimpleFoam(compressible),DARhoSimpleCFoam(compressible/transonic), andDAHisaFoam(compressible/transonic/supersonic). Leave unset,null, ornoneto use the default Mach-based selection.transonic_mach_boundary(float, default: 0.4): transonic Mach split used by the default solver selection whensolver_nameis not set.turbulence_model(str, default: “SpalartAllmaras”): OpenFOAM RANS turbulence model. Supported values areSpalartAllmaras(SA) andkOmegaSST(SST).u_plot_bounds(list[float], default: [-1.0, 1.0]): [Lower, upper] bounds of the normalized velocity colorbar for the U flow-field plot.struct_material(str, default: “aluminum”): structural material. Currently onlyaluminumis supported.nlbgs_rel_tol_orders_thresholds(list[float], default: [0.0, 2.0]): [Pass, Warning] thresholds for final relative NLBGS tolerance drop in log10 orders.nlbgs_abs_tol_orders_thresholds(list[float], default: [0.0, 2.0]): [Pass, Warning] thresholds for final absolute NLBGS tolerance drop in log10 orders.cd_delta_thresholds(list[float], default: [1e-5, 0.001]): [Pass, Warning] thresholds for absolute CD delta between coupled iterations.cl_delta_thresholds(list[float], default: [0.0001, 0.01]): [Pass, Warning] thresholds for absolute CL delta between coupled iterations.
adjoint_residual_drop_orders_thresholds(list[float], default: [5.0, 3.0]): [Pass, Warning] thresholds for minimum adjoint residual drop in log10 orders.camera_scale(float, default: 1.0): camera zoom multiplier for the 3D mesh and flow-field plots. Values below 1.0 zoom in, values above 1.0 zoom out; 1.0 is the default framing.cst_coeffs(list[float], default: null): user-supplied wing CST coefficients, ordered section by section as[upper..., lower...].len(cst_coeffs)must equal2 * profile_fit_coeff_count * number_of_sections. Set this only to parameterize the wing sections with explicit numeric CST values; leave it null (default) to use the named profiles inairfoil_profiles.cp_plot_bounds(list[float], default: [-2.0, 2.0]): [Lower, upper] bounds of the Cp axis and colorbar shared by the pressure-profile and Cp flow-field plots.dv_bounds(dict[str, list[float]], default: {“CSTCoeffs”: [-0.4, 0.4], “Twist”: [-5.0, 5.0], “Sweep”: [-15.0, 15.0], “Dihedral”: [0.0, 5.0], “AoA”: [0.0, 10.0], “Span”: [0.5, 1.5], “Chord”: [0.5, 1.5], “Wing_Root_Chord”: [1.0, 1.0]}): design-variable lower/upper bounds shared by EGO and regular optimization. All keys are required. Span, Chord (section tip chords), and Wing_Root_Chord (root chord of the whole wing) are multipliers of the baseline value, e.g. [0.9, 1.1] is +-10%; all other keys are absolute values (degrees for Twist, Sweep, Dihedral, AoA). Wing_Root_Chord defaults to be fixed with bounds [1.0, 1.0].final_feasibility_thresholds(list[float], default: [0.0001, 0.01]): [Pass, Warning] thresholds for final feasibility.flow_residual_drop_orders_thresholds(list[float], default: [6.0, 3.0]): [Pass, Warning] thresholds for minimum flow residual drop in log10 orders.max_adj_iters(int, default: 1000): maximum GMRES iterations used by the DAFoam adjoint linear solve.nlbgs_abs_tol(float, default: 2.0): absolute tolerance for the aerostructural OpenMDAONonlinearBlockGSnonlinear block Gauss-Seidel solver.nlbgs_rel_tol(float, default: 1e-7): relative tolerance for the aerostructural OpenMDAONonlinearBlockGSnonlinear block Gauss-Seidel solver.objective_reduction_pct_thresholds(list[float], default: [5.0, 1.0]): [Pass, Warning] thresholds for objective reduction in percent.pc_fill_level(int, default: 1): ILU fill level used by the DAFoam adjoint preconditioner.pressure_profile_fractions(list[float], default: [0.1, 0.5, 0.9]): spanwise fractions used for wing pressure-profile plots, for example[0.2, 0.4, 0.8].primal_func_slope_tol(float, default: 0.0001): DAFoam primal function slope tolerance passed to script_run_dafoam.py.primal_func_std_tol(float, default: 0.05): DAFoam primal function standard deviation tolerance passed to script_run_dafoam.py.primal_min_iters(int, default: 100): minimum number of primal iterations. This also sets thenStepswindow used by the primal function standard deviation convergence check.profile_fit_coeff_count(int, default: 6): number of coefficients used to fit each airfoil surface. For example,4fits 4 coefficients for the upper surface and 4 for the lower surface.solver_name(str, default: null): explicit solver override. Supported values areDASimpleFoam(incompressible),DARhoSimpleFoam(compressible),DARhoSimpleCFoam(compressible/transonic), andDAHisaFoam(compressible/transonic/supersonic). Leave unset,null, ornoneto use the default Mach-based selection.transonic_mach_boundary(float, default: 0.4): transonic Mach split used by the default solver selection whensolver_nameis not set.turbulence_model(str, default: “SpalartAllmaras”): OpenFOAM RANS turbulence model. Supported values areSpalartAllmaras(SA) andkOmegaSST(SST).u_plot_bounds(list[float], default: [-1.0, 1.0]): [Lower, upper] bounds of the normalized velocity colorbar for the U flow-field plot.struct_material(str, default: “aluminum”): structural material. Currently onlyaluminumis supported.dv_bounds_structure(dict[str, list[float]], default: {“PanelThickness”: [0.002, 0.05], “StiffenerHeight”: [0.01, 1.0], “StiffenerThickness”: [0.002, 0.05]}): structural sizing design-variable lower/upper bounds in meters (absolute values). All keys are required.n_multi_start(int, default: 20): number of multi-start points for the EGO internal EI optimization.ei_tol(float, default: 0.0001): EGO internal expected improvement (EI) optimization tolerance.ego_seed(int, default: 0): random seed used by the EGO optimizer DOE and infill sampling.ego_tol(float, default: 0.001): objective variation tolerance for the EGO optimization.ego_cstr_tol(float, default: 0.001): constraint tolerance used by EGO.
Agent Capability demos
CFD Mesh Generation
Users can prompt to generate wing CFD mesh with desired airfoil profiles, chords, sweeps, twists, dihedral, and span. For example,
Generate a cfd mesh for a wing with naca4412 at the root and naca0012 at the tip. The root chord is 1 m and the tip chord is 0.5 m. The tip twist is 1 deg. The semi-span is 3 m. The sweep is 10 degs. Mesh size 200K, yPlus 50.
The following is the AI generated pictures.
Fig. 1. Left: Overview of the generated CFD mesh. Right: Trame interactive view of the CFD mesh.
CFD-based Aerodynamic Simulation
Users can prompt to run wing CFD simulations with desired Mach number, Reynolds number, and angle of attack. For example,
Generate a cfd mesh for a wing with RAE2822 airfoils. The root chord is 1 m and the tip chord is 0.5 m. The sweep is 15 degs, and the semi span is 4 m. The tip twist is 1 deg. After that, run a cfd with aoa=3degs, The ref mach is 0.8 and the ref re is 1e7.
The following is the AI generated pictures.
Fig. 2. Left: Pressure profile from the CFD simulation. Right: Trame interactive view of the pressure contour.
FEA Mesh Generation
Users can prompt to generate wing FEA mesh with desired ribs, spars, and the coverage of the wingbox in chordwise and spanwise direction. For example,
Generate a cfd mesh for a wing with naca4412 at the root and naca0012 at the tip. The root chord is 1 m and the tip chord is 0.5 m. The tip twist is 1 deg. The semi-span is 3 m. The sweep is 10 degs. Mesh size 200K, yPlus 50. Also generate a FEA mesh for this wing with 2 spars and 10 ribs. The total element is about 3000. The wingbox starts and ends from 20% to 80% chord and extends to 90% span.
The following is the AI generated pictures.
Fig. 3. Left: Overview of the generated FEA mesh. Right: Trame interactive view of the FEA mesh.
CFD+FEA-based Aero-structural Simulation
Users can prompt to run wing aero-structural simulations with desired Mach number, Reynolds number, and angle of attack. For example, you can follow the above FEA mesh generation chat session and ask
Run an aero-structural simulation for this wing with aoa=4 degs, ma 0.3, re 5e6. Use 4 cores
The following is the AI generated pictures.
Fig. 4. Left: Flow residual of the aero-structural coupled simulation. Right: Trame interactive view of the von-Mises stress of the wing box.
Aerodynamic Shape Optimization
Users can prompt to run wing aerodynamic shape optimization with desired Mach number, Reynolds number, and target lift constraint. For example,
Generate a CFD mesh for the wing with 100K cells. Then, run an aerodynamic optimization with Ma=0.3, Re=5e6, and CL=0.3. Run for 50 iterations. Use 48 cores.
The case ran on the HPC. After it is finished, you need to resume the chat and ask it to analyze the optimization. The following is the AI generated pictures.
Fig. 5. Top: Optimization convergence history for CD and CL. Bot left: pressure profiles. Bot right: trame server view.