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What the Airfoil Agent Does

The airfoil agent supports these skills:

  • generate-cfd-mesh: build CFD mesh and mesh-quality outputs.
  • run-cfd-simulation: run steady CFD from an existing mesh.
  • run-aero-optimization: run single-point aerodynamic optimization.

Standard Inputs

generate-cfd-mesh (click to expand)

  • airfoil_profile (str, default: naca0012): airfoil name (for example naca0012, rae2822).
  • mesh_cells (int, default: 6000): target total mesh cell count.
  • y_plus (float, default: 50.0): near-wall mesh target in wall units.
  • mach_number (float, default: 0.3): freestream Mach number used for mesh sizing.
  • local_refine_box (list[list[float]], default: [[1.0, -0.2, -0.1], [2.0, 0.2, 0.1]]): two box-corner vectors [[x0, y0, z0], [x1, y1, z1]] used for the always-on single-level local refinement.

run-cfd-simulation (click to expand)

  • angle_of_attack (float, default: 2.0): angle of attack in degrees.
  • airfoil_profile (str, default: inherited from mesh step): profile name used for CST fitting when needed.
  • mach_number (float, default: inherited from mesh step): freestream Mach number.
  • solver_name (str, default: None): optional explicit solver override.
  • max_flow_iters (int, default: 3000): maximum solver iterations.
  • n_cst_coeffs (int, default: 6): number of CST coefficients per surface.
  • reynolds_number (float, default: 1000000.0): Reynolds number.
  • cst_coeffs (list[float], default: None): optional CST vector [upper..., lower...]; if omitted, it is fitted automatically.
  • n_cpu_cores (int, default: 1): MPI ranks/CPU cores.

run-aero-optimization (click to expand)

  • angle_of_attack (float, default: 2.0): initial angle of attack in degrees.
  • airfoil_profile (str, default: inherited from mesh step): airfoil profile.
  • mach_number (float, default: inherited from mesh step): freestream Mach number.
  • solver_name (str, default: None): optional solver override.
  • n_cst_coeffs (int, default: 6): CST coefficients per surface.
  • reynolds_number (float, default: 1000000.0): Reynolds number.
  • optimizer (str, default: IPOPT): optimizer (IPOPT, SNOPT, SLSQP).
  • lift_constraint (float, default: 0.5): minimum lift coefficient target.
  • max_opt_iters (int, default: 20): max optimization iterations.
  • thickness_constraint (float, default: 0.5): minimum normalized thickness (negative disables).
  • le_radius_constraint (float, default: -1.0): minimum normalized leading-edge radius (negative disables).
  • cst_coeffs (list[float], default: None): optional initial CST vector.
  • n_cpu_cores (int, default: 1): MPI ranks/CPU cores.

Advanced Parameters

generate-cfd-mesh (click to expand)

  • blunt_te (float, default: 0.01): trailing-edge round percentage expressed as an x/chord trim location; 0.01 means the trim starts at x = 0.01 from the trailing edge.
  • d0 (float, default: -1.0): first-layer height in meters; use a negative value to estimate it from y_plus and mach_number.
  • hyperbolic_sweeps (int, default: 20): number of smoothing sweeps per layer for hyperbolic extrusion.
  • neighbor_rings (int, default: 5): neighbor-ring depth used by the hyperbolic extrusion smoother.
  • diffuse_start (float, default: 0.002): smoothing onset distance in meters for hyperbolic diffusion.
  • 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: 5000.0): 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.

run-cfd-simulation (click to expand)

  • transonic_mach_boundary (float, default: 0.4): Mach-number boundary used by the default Mach-based solver selection when solver_name is not provided.
  • 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: 4.0): warning threshold for minimum residual drop in log10 orders.

run-aero-optimization (click to expand)

  • transonic_mach_boundary (float, default: 0.4): Mach-number boundary used by the default Mach-based solver selection when solver_name is not provided.
  • 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: 7.0): pass threshold for minimum flow residual drop in log10 orders.
  • flow_residual_drop_orders_warning (float, default: 5.0): 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

Mesh Generation

Users can prompt to generate airfoil mesh with desired airfoil profiles, mesh densities, yPlus, and local refinement.

Fig. 1. Top left: Overview of a coarse mesh. Prompt: Generate a cfd mesh for the naca0012 airfoil. Top right: Trame interactive view of the TE mesh. Bottom left: Overview of a fine mesh with a different airfoil. Prompt: Generate a cfd mesh for the rae2822 airfoil with 50K cells, yPlus 3, and ref Mach=0.7. Bottom right: Locally refined mesh. Prompt: Locally refine the above mesh between -0.1 to 1.1 chords from LE, z length of the refinment is 0.5 chords.

CFD Simulation

Users can prompt to run airfoil CFD simulations with desired airfoil profiles (prescribed in the mesh generation skill), angles of attack, Mach numbers, and Reynolds numbers.

Fig. 1. Left: Airfoil pressure profile. Prompt: Generate a cfd mesh for the naca0012 airfoil and run a cfd simulation at Ma=0.3, Re=5e6, and aoa=3 degs. Use 2 CPU cores. Right: Visualization of airfoil turbulence variable field in the trame interactive server.

CFD Mesh Convergence Study

Users can prompt to conduct a mesh convergence study for an airfoil.