Function veloren_common::comp::fluid_dynamics::lift_slope

fn lift_slope(aspect_ratio: f32, sweep_angle: Option<f32>) -> f32

The change in lift over change in angle of attack¹. Multiplying by angle of attack gives the lift coefficient (for a finite wing, not aerofoil). Aspect ratio is the ratio of total wing span squared over planform area.

Notes

Only valid for symmetric, elliptical wings at small² angles of attack³. Does not apply to twisted, cambered or delta wings. (It still gives a reasonably accurate approximation if the wing shape is not truly elliptical.)

1. geometric angle of attack, i.e. the pitch angle relative to freestream flow
2. up to around ~18°, at which point maximum lift has been achieved and thereafter falls precipitously, causing a stall (this is the stall angle)
3. effective aoa, i.e. geometric aoa - induced aoa; assumes no sideslip