Tests were made in Princeton University Helium Hypersonic Wind Tunnel at Mach number 11.8 and at Reynolds numbers based on leading edge thickness ranging from 4200 to 28,000; leading edges of models were swept back at angles of 60 and 70° and had thicknesses of 0.0005 and 0.030 in.; resulting data were analyzed, and pressure measurements, correlated with viscous interaction parameter, were evaluated using conical flow properties.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Some experiments on delta wings in hypersonic flow


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Barber, E.A. (Autor:in)

    Erschienen in:

    AIAA Journal ; 4 , n 1


    Erscheinungsdatum :

    1966


    Format / Umfang :

    12 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :



    Solutions for hypersonic viscous flow over delta wings

    RUFFIN, STEPHEN / MURMAN, EARLL | AIAA | 1988



    Experiments with hypersonic turbulent boundary layers on flat plates and delta wings

    Bertram, M. H. / Cary, A. M., Jr. / Whitehead, A. H., Jr. | NTRS | 1968


    Experiments with Hypersonic Turbulent Boundary Layers on Flat Plates and delta Wings

    M. H. Bertram / A. M. Cary / A. H. Whitehead | NTIS | 1968