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.


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    Title :

    Aerodynamic and heating problems of advanced reentry vehicles


    Additional title:

    NASA -- Proc


    Contributors:
    Trimpi, R.L. (author) / Grant, F.C. (author) / Cohen, N.B. (author)

    Conference:

    NASA -- University Conference on Science and Technology of Space Exploration ; 1962 Re-entry



    Publication date :

    1962


    Size :

    14 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English


    Keywords :



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