Analyze Naca
analyze_nacaComputes an aerodynamic polar for any NACA 4/5-digit airfoil and uses XFOIL to generate geometry, avoiding library edits.
Instructions
Compute a polar for any NACA 4/5-digit airfoil without touching the library (XFOIL generates the geometry itself).
Tool call template
Replace each placeholder with a value matching the input schema. Only required parameters are included; add optional parameters as needed.
{
"id": 1,
"jsonrpc": "2.0",
"method": "tools/call",
"params": {
"arguments": {
"naca_code": "<naca_code>"
},
"name": "analyze_naca"
}
}Input Schema
| Name | Required | Description | Default |
|---|---|---|---|
| re | No | ||
| mach | No | ||
| ncrit | No | ||
| alfa_end | No | ||
| alfa_step | No | ||
| naca_code | Yes | ||
| alfa_start | No | ||
| install_dir | No |
Output Schema
| Name | Required | Description | Default |
|---|---|---|---|
| result | Yes |