pub fn expansion_pressure_coefficient(
mach: f64,
turn_rad: f64,
) -> Result<f64, AeroError>Expand description
The pressure coefficient behind a two-dimensional isentropic (Prandtl–Meyer) expansion of a
flow at Mach mach ≥ 1 through turn_rad: M₂ from ν(M₂) = ν(M) + θ, then
C_p = (p₂/p − 1)/(γ M²/2) with p₂/p = [(1 + (γ−1)M²/2)/(1 + (γ−1)M₂²/2)]^(γ/(γ−1))
(NACA Report 1135: the pressures from eq. 44, the dynamic pressure γ p M²/2 from eq. 31b,
p. 616). Past the largest turning angle the flow reaches a vacuum, C_p = −2/(γ M²).
§Errors
AeroError::Domain below Mach 1, for a non-finite Mach number, or a turning angle outside
[0, π/2].