Re-entry of manned lifting vehicles at parabolic (escape) velocity and of unmanned nonlifting planetary probes at hyperbolic velocities are considered; spatial and temporal convective and radiation heating distributions are predicted for lifting spacecraft of Apollo class; preliminary study of effects of heat of sublimation on limiting entry velocity, ratio of payload to total weight on limiting entry velocity, and size and total weight of re-entry vehicle necessary to return specific payload to earth at given high re-entry velocity.
Aerodynamic and heating problems of advanced reentry vehicles
NASA -- Proc
NASA -- University Conference on Science and Technology of Space Exploration ; 1962 Re-entry
1962
14 pages
Conference paper
English
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