Note: Please follow the instructions from the Overview page to install MDO Agent Deck before using the aircraft agent.
What the Aircraft Agent Does
The aircraft agent supports these skills:
generate-cfd-mesh: build the aircraft CFD mesh and mesh-quality outputs.run-cfd-simulation: run steady aircraft CFD from an existing mesh.run-aero-optimization: run aerodynamic shape optimization for the aircraft.
Standard Inputs
airfoil_profiles(list[str], default: [“rae2822”, “rae2822”, “rae2822”]): wing airfoil profile names ordered section 0 to section 2.sweeps(list[float], default: [35.0, 30.0]): wing sweep angles in degrees formatted as [break_sweep_deg, tip_sweep_deg].twists(list[float], default: [0.0, 0.0]): wing twist angles in degrees formatted as [section1_twist_deg, section2_twist_deg].chords(list[float], default: [8.0, 4.5, 1.7]): wing chord lengths for the packaged geometry.spans(list[float], default: [5.0, 14.0]): wing panel semi-span values.dihedrals(list[float], default: [6.0, 6.0]): wing dihedral angles in degrees.tail_twist(float, default: 0.0): tail twist angle in degrees.n_cpus(int, default: 2): MPI ranks used for the parallel snappyHexMesh passes.surface_level(int, default: 7): snappyHexMesh surface refinement level.n_boundary_layers(int, default: 8): number of prism layers.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.
angle_of_attack(float, default: 2.0): freestream angle of attack in degrees.mach_number(float, default: 0.3): freestream Mach number.reynolds_number(float, default: 1000000.0): freestream Reynolds number.airfoil_profiles(list[str], default: inherited from generate-cfd-mesh): wing airfoil profiles used for CST fitting when needed.cst_coeffs(list[float], default: None): optional flattened aircraft wing CST coefficient vector.chords(list[float], default: inherited from generate-cfd-mesh): wing chord values.spans(list[float], default: inherited from generate-cfd-mesh): wing semi-span values.sweeps(list[float], default: inherited from generate-cfd-mesh): wing sweep values.twists(list[float], default: inherited from generate-cfd-mesh): wing twist values.dihedrals(list[float], default: inherited from generate-cfd-mesh): wing dihedral values.tail_twist(float, default: inherited from generate-cfd-mesh): tail twist angle.pressure_profile_fractions(list[float], default: [0.2, 0.5, 0.9]): spanwise fractions used for pressure-profile plots.n_cpu_cores(int, default: 1): MPI ranks/CPU cores.
angle_of_attack(float, default: 2.0): initial freestream angle of attack in degrees.airfoil_profiles(list[str], default: inherited from generate-cfd-mesh): wing airfoil profiles used for CST fitting when needed.mach_number(float, default: inherited from generate-cfd-mesh): freestream Mach number.reynolds_number(float, default: 1000000.0): freestream Reynolds number.optimizer(str, default: “IPOPT”): optimization algorithm.lift_constraint(float, default: 0.5): target lift coefficient equality constraint.le_radius_constraint(float, default: 0.7): lower bound on normalized leading-edge radius.thickness_constraint(float, default: 0.5): lower bound on normalized aircraft wing thickness.volume_constraint(float, default: 1.0): lower bound on normalized aircraft wing volume.max_opt_iters(int, default: 100): maximum optimization iterations.cst_coeffs(list[float], default: None): optional flattened aircraft wing CST coefficient vector.chords(list[float], default: inherited from generate-cfd-mesh): wing chord values.sweeps(list[float], default: inherited from generate-cfd-mesh): wing sweep values.dihedrals(list[float], default: inherited from generate-cfd-mesh): wing dihedral values.spans(list[float], default: inherited from generate-cfd-mesh): wing semi-span values.twists(list[float], default: inherited from generate-cfd-mesh): wing twist values.tail_twist(float, default: inherited from generate-cfd-mesh): tail twist angle.pressure_profile_fractions(list[float], default: [0.2, 0.5, 0.9]): spanwise fractions used for pressure-profile plots.n_cpu_cores(int, default: 1): MPI ranks/CPU cores.
Advanced Parameters
max_cell_size(float, default: null): target farfieldblockMeshcell size used to size the outer box; if unset, the skill uses the mean wing chord.line_level(int, default: null): snappyHexMesh feature-edge refinement level; if unset, the skill usessurface_level + 1.curvature_level(int, default: null): snappyHexMesh curvature refinement level; if unset, the skill usessurface_level + 2, and-1disables curvature refinement.n_layer_outer_iter(int, default: 3): number of outer iterations used inaddLayersControls.max_nonorthogonality_pass(float, default: 70.0): pass threshold for maximum non-orthogonality.max_nonorthogonality_warning(float, default: 80.0): warning threshold for maximum non-orthogonality.max_aspect_ratio_pass(float, default: 1000.0): pass threshold for maximum aspect ratio.max_aspect_ratio_warning(float, default: 10000.0): warning threshold for maximum aspect ratio.max_skewness_pass(float, default: 4.0): pass threshold for maximum skewness.max_skewness_warning(float, default: 6.0): warning threshold for maximum skewness.
transonic_mach_boundary(float, default: 0.4): Mach boundary used by default solver selection.solver_name(str, default: null): explicit solver override; leave unset to use the default aircraft solver.max_flow_iters(int, default: 10000): maximum flow iterations written to the case control settings.primal_func_std_tol(float, default: 5e-3): DAFoam primal function standard deviation tolerance.primal_func_slope_tol(float, default: 1e-6): DAFoam primal function slope tolerance.n_cst_coeffs(int, default: 6): number of CST coefficients per surface used whenpreparefits CST coefficients.reference_area(float, default: null): aerodynamic reference area override; if unset, the skill uses mean chord times span.reference_length(float, default: null): aerodynamic reference length override; if unset, the skill uses the mean chord.coef_stddev_pct_pass(float, default: 0.001): pass threshold for force-coefficient standard deviation in percent.coef_stddev_pct_warning(float, default: 1.0): warning threshold for force-coefficient standard deviation in percent.residual_drop_orders_pass(float, default: 6.0): pass threshold for minimum residual drop in log10 orders.residual_drop_orders_warning(float, default: 3.0): warning threshold for minimum residual drop in log10 orders.
transonic_mach_boundary(float, default: 0.4): Mach boundary used by default solver selection.solver_name(str, default: null): explicit solver override; leave unset to use the default aircraft solver.max_flow_iters(int, default: 10000): maximum flow iterations written to the case control settings.primal_func_std_tol(float, default: 5e-3): DAFoam primal function standard deviation tolerance.primal_func_slope_tol(float, default: 1e-6): DAFoam primal function slope tolerance.n_cst_coeffs(int, default: 6): number of CST coefficients per surface used whenpreparefits CST coefficients.reference_area(float, default: null): aerodynamic reference area override; if unset, the skill uses mean chord times span.reference_length(float, default: null): aerodynamic reference length override; if unset, the skill uses the mean chord.objective_reduction_pct_pass(float, default: 5.0): pass threshold for objective reduction in percent.objective_reduction_pct_warning(float, default: 1.0): warning threshold for objective reduction in percent.final_feasibility_pass(float, default: 0.0001): pass threshold for final feasibility.final_feasibility_warning(float, default: 0.01): warning threshold for final feasibility.flow_residual_drop_orders_pass(float, default: 6.0): pass threshold for minimum flow residual drop in log10 orders.flow_residual_drop_orders_warning(float, default: 3.0): warning threshold for minimum flow residual drop in log10 orders.adjoint_residual_drop_orders_pass(float, default: 5.0): pass threshold for minimum adjoint residual drop in log10 orders.adjoint_residual_drop_orders_warning(float, default: 3.0): warning threshold for minimum adjoint residual drop in log10 orders.
Agent Capability demos
CFD Mesh Generation
Users can prompt to generate an aircraft CFD mesh with the pre-defined model (wing+fuselage+tails). The default model is similar to Boeing 737 and users can prescribe the desired wing sectional airfoil profiles, chords, sweeps, twists, dihedral, span, as well as the vertical tail rotation. For example, Generate a cfd mesh for the default aircraft configuration. Use 8 cores The following is the AI generated pictures.
Fig. 1. Left: The default aircraft geometry. Right: Overview of the generated CFD mesh.
CFD-based Aerodynamic Simulation
Users can prompt to run CFD simulations for the aircraft with desired Mach number, Reynolds number, and angle of attack. For example, Generate a cfd mesh for the default aircraft configuration. After that, run a cfd with aoa=2degs, The mach is 0.85 and the ref re is 2e7. The following is the AI generated pictures.
Fig. 2. Left: Pressure profile from the CFD simulation. Right: Trame interactive view of the pressure contour.