wing_vlm_analysis
Analyze wing aerodynamics using Vortex Lattice Method to compute lift, drag, pitching moment, and L/D ratio at multiple angles of attack.
Instructions
Analyze wing aerodynamics using Vortex Lattice Method or simplified lifting line theory.
Args: wing_config: Wing configuration with keys: - span_m: Wing span in meters - chord_root_m: Root chord in meters - chord_tip_m: Tip chord in meters (optional, defaults to chord_root_m) - sweep_deg: Quarter-chord sweep in degrees (optional, default 0) - dihedral_deg: Dihedral angle in degrees (optional, default 0) - twist_deg: Tip twist in degrees (optional, default 0) - airfoil_root: Root airfoil name (optional, default 'NACA2412') - airfoil_tip: Tip airfoil name (optional, default matches root) flight_conditions: Flight conditions with keys: - alpha_deg_list: List of angles of attack to analyze (required) - mach: Mach number (optional, default 0.2) - reynolds: Reynolds number (optional) analysis_options: Optional analysis settings (currently unused)
Returns: Formatted string with aerodynamic analysis results including CL, CD, CM, and L/D ratio at each angle of attack.
Raises: No exceptions are raised directly; errors are returned as formatted strings. ImportError is caught when aerodynamics packages are not installed.
Note: The Vortex Lattice Method (VLM) discretizes the wing planform into panels, each modeled with a horseshoe vortex. Each horseshoe vortex consists of a bound vortex along the panel quarter-chord line and two trailing (semi-infinite) vortices extending downstream. The induced velocity at each panel's 3/4-chord control point is computed via the Biot-Savart law, and the no-penetration boundary condition is enforced to solve for the vortex strengths (circulation distribution).
Input Schema
| Name | Required | Description | Default |
|---|---|---|---|
| wing_config | Yes | ||
| flight_conditions | Yes | ||
| analysis_options | No |
Output Schema
| Name | Required | Description | Default |
|---|---|---|---|
| result | Yes |