xfoil.compute_polar
Calculate airfoil lift and drag coefficients by running XFOIL analysis with specified Reynolds number and angle of attack sweep parameters.
Instructions
Run XFOIL for an airfoil at specified Reynolds angle of attack sweep. Input airfoil coordinates or NACA code plus sweep parameters. Returns lift/drag polar tables and solver metadata.
Input Schema
| Name | Required | Description | Default |
|---|---|---|---|
| request | Yes |
Input Schema (JSON Schema)
{
"properties": {
"request": {
"$ref": "#/$defs/PolarRequest"
}
},
"required": [
"request"
],
"type": "object"
}