calculate_lift_force
Calculate lift force for aircraft wings and aerodynamic surfaces using the standard lift equation L = ½ρv²CₗA, accounting for velocity, wing area, lift coefficient, and fluid density.
Instructions
Calculate lift force using: L = (1/2) ρ v² C_L A.
Based on Bernoulli's principle and wing aerodynamics.
Args:
velocity: Flow velocity in m/s
wing_area: Wing area in m²
lift_coefficient: Lift coefficient C_L (dimensionless)
fluid_density: Fluid density in kg/m³ (air=1.225)
Returns:
Dict containing:
- lift_force: Lift force in Newtons
- dynamic_pressure: Dynamic pressure (q) in Pascals
Example - Aircraft wing:
result = await calculate_lift_force(
velocity=70, # m/s (~250 km/h)
wing_area=20.0, # m²
lift_coefficient=1.2,
fluid_density=1.225
)Input Schema
TableJSON Schema
| Name | Required | Description | Default |
|---|---|---|---|
| velocity | Yes | ||
| wing_area | Yes | ||
| lift_coefficient | Yes | ||
| fluid_density | No |