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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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


    Additional title:

    NASA -- Memo


    Contributors:


    Publication date :

    1959


    Size :

    15 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :