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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    Title :

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


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1959


    Size :

    59 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :