A 65 deg 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 a systematic variation of the leading edge bluntness. The analysis for this paper is focused on the Reynolds number and bluntness effects at transonic speeds (M = 0.85) from this data set. The results show significant effects of both these parameters on the onset and progression of leading- edge vortex separation.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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


    Contributors:

    Publication date :

    2003-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :