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 compressibility and bluntness effects primarily at a Reynolds number of 6 million from this data set. Emphasis is placed upon on the onset and progression of leading-edge vortex separation, and compressibility is shown to promote this separation. Comparisons with recent publications show that compressibility and Reynolds number have opposite effects on blunt leading edge vortex separation


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    Title :

    Compressibility and Leading-Edge Bluntness Effects for a 65 Deg Delta Wing


    Contributors:

    Conference:

    42nd AIAA Aerospace Sciences Meeting and Exhibit ; 2004 ; Reno, NV, United States


    Publication date :

    2004-01-01


    Type of media :

    Preprint


    Type of material :

    No indication


    Language :

    English





    Compressibility and Leading-Edge Bluntness Effects for a 65^o Delta Wing

    Luckring, J. M. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2004




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    Lhopiteau, Charles / Proença, Anderson R. / Garry, Kevin P. | AIAA | 2025