The aerodynamic heating of a super orbital reentry capsule for MUSES-C is numerically studied by using full viscous-shock-layer (VSL) equations with an 11 air-species model. With a three-temperature model, the thermal nonequilibrium effect is considered. Temperatures, chemical species, and energy exchange rates at three typical altitudes, 74 km, 64 km, and 54 km, are discussed to understand how thermochemical nonequilibrium phenomena change along the reentry trajectory path. The convective and radiative heat fluxes to the wall of the MUSES-C capsule with a 0.2 m nose radius are examined under both noncatalytic wall (NCW) and fully catalytic wall (FCW) conditions. The maximum heat fluxes estimated for FCW and NCW are 8.7 MW/m² and 6.1 MW/m² at the altitude of 56 km. The radiative heat flux at the stagnation point of the capsule has also been calculated, and the maximum radiative heat flux of 0.9 MW/m² has been found at the altitude of 62 km. The intensity of UV and VUV spectra are extremely intense; thus UV and VUV spectra mainly contribute to the radiative heat flux.