Application of spikes ahead of blunt noses of bodies of revolution as means of drag reduction; results of heat transfer and pressure tests, obtained in Langley hypersonic wind tunnel are presented together with study of effect of transition position; where possible, separation phenomena is compared with available theory; Schlieren photographs.


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    Titel :

    Investigation of flow over spiked-nose hemisphere-cylinder at mach number of 6.8


    Weitere Titelangaben:

    NASA -- Tech Note


    Beteiligte:
    Crawford, D.H. (Autor:in)


    Erscheinungsdatum :

    1959


    Format / Umfang :

    59 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :