aerodynamic-heatinglisted

# Aerodynamic Heating (aerodynamics/high-speed/aerodynamic-heating) Use when you must estimate the aerodynamic heating at the stagnation point of a hypersonic body: correlation-level convective heating from the Sutton-Graves model, the radiation-equilibrium wall temperature it implies, and the nose-radius bluntness trade that drives thermal protection material selection. This leaf implements the Sutton-Graves stagnation-point correlation and the Stefan-Boltzmann radiation balance in pure Python, stdlib only, for flight at a fixed point (constant freestream density and velocity). It pairs with aerodynamics/high-speed/hypersonic-flow for the hypersonic flight environment context and with structures/thermal-structures/thermal-stress-analysis when the wall temperature feeds a structural thermal analysis. ## Domain quick reference - Sutton-Graves stagnation heat flux: q_s = C_SG * sqrt(rho / R_n) * V**3, with C_SG = 1.83e-4 (air correlation constant, SI units arranged so q_s is in W/m2), rho the freestream density in kg/m3, R_n the nose radius in m and V the flight velocity in m/s. The correlation captures the convective heating of the thin shock layer ahead of a blunt body at hypersonic speed. - Radiation-equilibrium wall temperature: T_w = (q / (eps * sigma))**0.25, from the steady balance q = eps * sigma * T_w**4 with sigma = 5.670374419e-8 W/m2/K4 (Stefan-Boltzmann) and eps the surface emissivity, default 0.85 for typical thermal protection surfaces. - Nose-