Hypersonic Reentry Stagnation Point Heat Transfer Calculator
Model convective aerodynamic heat flux (W/cm²), radiative equilibrium surface temperature, and Thermal Protection System (TPS) limits using the Fay-Riddell formulation.
Reentry Vehicle Geometry & Trajectory
Apollo ~ 4.7m; Space Shuttle ~ 0.66m
LEO ~ 7.8 km/s; Lunar ~ 11.2 km/s
Stagnation Thermal Loading & Equilibrium Temp
Stagnation Heat Flux (q_s):
—
— Btu/ft²·s
Radiative Equilibrium Surface Temp:
—
— °F
Free-Stream Air Density (ρ_inf):
—
Total Stagnation Enthalpy (h0):
— MJ/kg
TPS Material Compatibility:
—
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