Investigation of supersonic diffuser throat area at Mach numbers 1.4, 1.8, and 3.5 with tunnel empty.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Flow structure and pressure recovery in supersonic open jet wind tunnel


    Additional title:

    Canada. Nat Aeronautical Establishment -- Note


    Contributors:
    Hall, J.G. (author)


    Publication date :

    1952


    Size :

    39 pages


    Remarks:

    Illus, Diagrs, Charts, Tables


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Pressure response in supersonic wind-tunnel pressure instrumentation

    Ducoffe, A.L. | Engineering Index Backfile | 1953


    Supersonic wind tunnel optimization

    BUSHNELL, D. / TRIPI, R. | AIAA | 1986


    Continuous supersonic wind tunnel

    Engineering Index Backfile | 1955



    Continuous supersonic wind tunnel

    Engineering Index Backfile | 1955