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.


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    Title :

    Some experiments on delta wings in hypersonic flow


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 4 , n 1


    Publication date :

    1966


    Size :

    12 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



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