Results of tests conducted in Ames low density wind tunnel and surface pressures measured for Mach number of 5.7 and Reynolds number per inch of 20,000; pressure distributions evidenced no appreciable 3-dimensional effects and were predicted qualitatively by method described for calculation in 2-dimensional flow.


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    Titel :

    Surface pressure distribution at hypersonic speeds for blunt Delta wings at angle of attack


    Weitere Titelangaben:

    NASA -- Memo


    Beteiligte:
    Creager, M.O. (Autor:in)


    Erscheinungsdatum :

    1959


    Format / Umfang :

    15 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :