Approximate analysis for effect of arbitrarily-distributed blowing on laminar boundary layer flow and pressure distribution around two-dimensional or axially-symmetric hypersonic blunt bodies; analysis is based on simplified integral method solution coupled with Newtonian model of inviscid flow around effective body shape defined by dividing streamline between blown and free stream gas; significant increases in local pressure are found when blowing is continued around nose into afterbody region. (32622)


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    Title :

    Effect of gaseous injection on aerodynamics of transpiration-cooled hypervelocity bodies


    Additional title:

    ASME -- Aviation and Space -- Progress and Prospects


    Contributors:
    Inger, G.R. (author) / Sayano, S. (author)

    Conference:

    ASME -- Annual Aviation and Space Conference ; 1968 ; United States , Beverly Hills, CA Hypersonic flow



    Publication date :

    1968


    Size :

    8 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English


    Keywords :



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