pub fn stagnation_pressure_ratio(mach: f64) -> Result<f64, AeroError>Expand description
Stagnation-pressure ratio q_stag/q (Niskanen 2009 eq. B.1, after Hoerner pp. 15-2, 16-3):
1 + M²/4 + M⁴/40 below Mach 1 and 1.84 − 0.76/M² + 0.166/M⁴ + 0.035/M⁶ from Mach 1 (1.275
and 1.281 at M = 1).
§Errors
AeroError::Domain for a negative or non-finite Mach number.