The Radiative Gas Dynamics of the Apollo-4 Command Module during Superorbital Earth Entry

The problem of the radiative gas dynamics of superorbital entry of the Apollo-4 command module into the Earth’s dense atmosphere has been numerically solved in the two-dimensional formulation of the flow around the front aerodynamic shield in the velocity range of the entry into the Earth’s dense at...

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Bibliographic Details
Published in:Fluid dynamics 2022-12, Vol.57 (Suppl 2), p.S515-S543
Main Author: Surzhikov, S. T.
Format: Article
Language:English
Subjects:
Apollo spacecraft
Atmospheric entry
Classical and Continuum Physics
Classical Mechanics
Command modules
Engineering Fluid Dynamics
Fluid- and Aerodynamics
Gas dynamics
Heat flux
Nonequilibrium flow
Physics
Physics and Astronomy
Segments
Thermal radiation
Trajectories
Two dimensional flow
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Summary:The problem of the radiative gas dynamics of superorbital entry of the Apollo-4 command module into the Earth’s dense atmosphere has been numerically solved in the two-dimensional formulation of the flow around the front aerodynamic shield in the velocity range of the entry into the Earth’s dense atmosphere V ∞ = 10.7–5.75 km/s and in the altitude range Н = 91.5–35.0 km. The specific trajectory segments with a strongly nonequilibrium flow in the shock layer, the most thermally loaded segments of the trajectory, and the segments with strong radiative-gasdynamic interaction in the relatively dense and highly rarefied oncoming flow have been determined. The distributions of densities of convective and radiative heat fluxes along the streamlined surface have been obtained. The spectral composition of the heat radiation has been studied. The calculation results have been successfully compared with the flight experimental data.
ISSN:0015-4628
1573-8507
DOI:10.1134/S0015462822100718