A 65 degree delta wing has been tested in the National Transonic Facility (NTF) at mean aerodynamic chord Reynolds numbers from 6 million to 120 million at subsonic and transonic speeds. The configuration incorporated systematic variation of the leading edge bluntness. The analysis for this paper is focused on the Reynolds number and bluntness effects at subsonic speeds (M = 0.4) from this data set. The results show significant effects of both these parameters on the onset and progression of leading-edge vortex separation.


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    Title :

    Reynolds Number and Leading-Edge Bluntness Effects on a 65 deg Delta Wing


    Contributors:

    Publication date :

    2002


    Size :

    20 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English