Aerodynamics
Analyze attached-flow wing circulation, explicit analytical airfoil models, and longitudinal static stability.
AS-AE-04
Available calculations.
- wing_vlm_analysis
- airfoil_polar_analysis
- calculate_stability_derivatives
- get_airfoil_database
Runner example.
The installed skill teaches your agent when to activate this module and how to call the local runner.
wing_vlm_analysisAS-AE-04
{
"ok": true,
"operation": "wing_vlm_analysis",
"result": {
"lift_coefficient": 0.416048,
"drag_coefficient": 0.0309961,
"induced_drag_coefficient": 0.0089961,
"lift_n": 8914.499,
"drag_n": 664.141,
"aspect_ratio": 7.46914,
"lift_to_drag": 13.4226,
"spanwise_circulation": [
{
"span_station_m": -5.47647,
"circulation_m2_s": 2.946714,
"sectional_lift_coefficient": 0.0970066
},
{
"span_station_m": -5.38277,
"circulation_m2_s": 5.0453749,
"sectional_lift_coefficient": 0.1648932
},
{
"span_station_m": -5.19696,
"circulation_m2_s": 7.1654392,
"sectional_lift_coefficient": 0.2308689
},
{
"span_station_m": -4.92224,
"circulation_m2_s": 9.1236964,
"sectional_lift_coefficient": 0.2879417
},
{
"span_station_m": -4.56329,
"circulation_m2_s": 10.9042145,
"sectional_lift_coefficient": 0.3351638
},
{
"span_station_m": -4.12627,
"circulation_m2_s": 12.5410653,
"sectional_lift_coefficient": 0.3736182
},
{
"span_station_m": -3.61864,
"circulation_m2_s": 14.0787609,
"sectional_lift_coefficient": 0.4049591
},
{
"span_station_m": -3.04909,
"circulation_m2_s": 15.5482397,
"sectional_lift_coefficient": 0.4305617
},
{
"span_station_m": -2.42738,
"circulation_m2_s": 16.954642,
"sectional_lift_coefficient": 0.4511562
},
{
"span_station_m": -1.76413,
"circulation_m2_s": 18.2694146,
"sectional_lift_coefficient": 0.466682
},
{
"span_station_m": -1.0707,
"circulation_m2_s": 19.4180488,
"sectional_lift_coefficient": 0.4760982
},
{
"span_station_m": -0.35895,
"circulation_m2_s": 20.242456,
"sectional_lift_coefficient": 0.4766583
},
{
"span_station_m": 0.35895,
"circulation_m2_s": 20.242456,
"sectional_lift_coefficient": 0.4766583
},
{
"span_station_m": 1.0707,
"circulation_m2_s": 19.4180488,
"sectional_lift_coefficient": 0.4760982
},
{
"span_station_m": 1.76413,
"circulation_m2_s": 18.2694146,
"sectional_lift_coefficient": 0.466682
},
{
"span_station_m": 2.42738,
"circulation_m2_s": 16.954642,
"sectional_lift_coefficient": 0.4511562
},
{
"span_station_m": 3.04909,
"circulation_m2_s": 15.5482397,
"sectional_lift_coefficient": 0.4305617
},
{
"span_station_m": 3.61864,
"circulation_m2_s": 14.0787609,
"sectional_lift_coefficient": 0.4049591
},
{
"span_station_m": 4.12627,
"circulation_m2_s": 12.5410653,
"sectional_lift_coefficient": 0.3736182
},
{
"span_station_m": 4.56329,
"circulation_m2_s": 10.9042145,
"sectional_lift_coefficient": 0.3351638
},
{
"span_station_m": 4.92224,
"circulation_m2_s": 9.1236964,
"sectional_lift_coefficient": 0.2879417
},
{
"span_station_m": 5.19696,
"circulation_m2_s": 7.1654392,
"sectional_lift_coefficient": 0.2308689
},
{
"span_station_m": 5.38277,
"circulation_m2_s": 5.0453749,
"sectional_lift_coefficient": 0.1648932
},
{
"span_station_m": 5.47647,
"circulation_m2_s": 2.946714,
"sectional_lift_coefficient": 0.0970066
}
]
},
"units": {
"lift_n": "N",
"drag_n": "N",
"span_station_m": "m",
"circulation_m2_s": "m^2/s"
},
"assumptions": [
"Steady incompressible potential flow",
"Flat mean-camber surface represented by horseshoe-vortex panels",
"Profile drag and Oswald efficiency are supplied separately"
],
"warnings": [
"Panel VLM is valid only for attached, low-speed flow at modest incidence; validate against geometry-appropriate CFD, wind-tunnel, or flight data"
],
"provenance": [
"Horseshoe-vortex lattice with Biot-Savart influence coefficients",
"U.S. Standard Atmosphere 1976"
]
}