normal-shocklisted

# Normal Shock Relations (aerodynamics/high-speed/normal-shock) Use when the task is the normal shock relations of compressible flow: downstream Mach number, static pressure, density, and temperature ratios, and the stagnation pressure loss across the shock, from the upstream Mach number M1 and the specific heat ratio gamma. ## Domain quick reference - All inputs are unitless: the upstream Mach number M1 (must be > 1, supersonic) and the specific heat ratio gamma (default 1.4 for air). - Downstream Mach: M2 = sqrt((1 + (gamma-1)/2 * M1^2) / (gamma * M1^2 - (gamma-1)/2)); M2 < 1 whenever M1 > 1. - Static pressure ratio: p2/p1 = 1 + 2*gamma/(gamma+1) * (M1^2 - 1), always > 1. - Density ratio: rho2/rho1 = ((gamma+1) * M1^2) / (2 + (gamma-1) * M1^2). - Temperature ratio: T2/T1 = (p2/p1) / (rho2/rho1), from the ideal-gas relation. - Stagnation pressure ratio: p02/p01 = (p2/p1)^(1/(1-gamma)) * (rho2/rho1)^(gamma/(gamma-1)), always < 1 for M1 > 1: the total pressure loss is the entropy gain of shock compression. - Textbook anchor (Anderson, Modern Compressible Flow, Table A.2) at M1 = 2.0, gamma = 1.4: M2 = 0.5773503, p2/p1 = 4.5, T2/T1 = 1.6875, rho2/rho1 = 2.6666667, p02/p01 = 0.720875. ## Workflow 1. Collect the upstream Mach number M1 and the specific heat ratio gamma (default 1.4 for air). 2. Compute the downstream Mach number with downstream_mach. 3. Compute the static ratios with pressure_ratio, density_ratio, and temperature_ratio. 4. Compute the