Three-Dimensional Problem of Radiative Gasdynamics of the Apollo-4 Command Module during Superorbital Atmospheric Entry

Abstract

The three-dimensional problem of radiative gasdynamics of the superorbital entry of the Apollo-4 command module into the dense terrestrial atmosphere at an angle of attack of 25° is numerically solved. The flow conditions corresponding to the flight velocity V_∞ = 10.5 km/s at an altitude H = 67.3 km are considered in detail. The distributions of the densities of convective and radiative heat fluxes along the surface in a flow are obtained. The spectral composition of the thermal radiation attaining the surface is studied. The results of the calculations are successfully compared with the data of two-dimensional calculations.