hypersonic-flowlisted

# Hypersonic Flow Forces (aerodynamics/high-speed/hypersonic-flow) Use when the task is estimating the aerodynamic forces on a body in hypersonic continuum flow with the classical modified Newtonian impact theory: the flow is fast enough (Mach well above 5) that the bow shock sits close to the body, so the surface pressure is set by the impact of freestream particles rather than by isentropic turning. The leaf computes the stagnation pressure behind the normal shock with the Rayleigh pitot relation, the finite-Mach stagnation pressure coefficient, the local pressure coefficient of a windward surface from its inclination (sine-squared law), the vacuum limit on shadowed surfaces, and the integrated force coefficients of a sphere, a sharp cone at zero incidence and an inclined flat plate. It pairs with aerodynamics/high-speed/normal-shock, the pitot-relation neighbor for the shock itself, and with the supersonic high-speed leaves, which own the regime below Mach ~ 5 where Newtonian methods hand over to shock-expansion and oblique-shock estimates. The method is the classical engineering estimate for hypersonic continuum flow, not a CFD replacement. Pure Python, stdlib only. ## Domain quick reference - Rayleigh pitot relation: p02/p1 = ((gamma+1)^2 * M^2 / (4*gamma*M^2 - 2*(gamma-1)))^(gamma/(gamma-1)) * (2*gamma*M^2 - gamma + 1) / (gamma+1). Stagnation pressure behind the normal shock over upstream static pressure at freestream Mach M, gamma = 1.4 by default. - Stagnatio