Method of integral relations is used to determine equilibrium air properties in subsonic and transonic portions of flowfield about body entering earth's atmosphere at hypersonic velocities and zero angle of attack; by interpolating certain quantities as linear functions between body and shock, equations of motion can be integrated across shock layer and replaced by set of ordinary differential equations that are solved by direct numerical integration along body; numerical results for small-scale Apollo vehicle at altitude of 171,111 ft and velocity of 34,582 fps are presented.


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    Title :

    Symmetrical, equilibrium flow past blunt body at superorbital re-entry speeds


    Additional title:

    AIAA J


    Contributors:
    Kuby, W. (author) / Foster, R.M. (author) / Byron, S.R. (author) / Holt, M. (author)

    Published in:

    AIAA Journal ; 5 , n 4


    Publication date :

    1967


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



    Symmetrical, equilibrium flow past a blunt body at superorbital re-entry speeds.

    Byron, S. R. / Foster, R. M. / Holt, M. et al. | NTRS | 1967



    Aerothermodynamics Behind a Blunt Body at Superorbital Speeds

    Park, Gisu / Gai, Sudhir L. / Neely, Andrew J. | AIAA | 2010


    Variable-lift re-entry at superorbital and orbital speeds

    Wang, H.E. / Chu, S.T. | Engineering Index Backfile | 1963