pub fn pitot_pressure_ratio(mach: f64) -> Result<f64, AeroError>Expand description
The pitot pressure behind a normal shock over the free stream’s, p_t2/p₀, at Mach mach
(the Rayleigh pitot formula, NACA Report 1135 eq. 100, p. 619; TN D-4865 eq. 1).
§Errors
AeroError::Domain for a Mach number that isn’t finite and above 1, or so large (past about
1e76) that the ratio overflows.