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.


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    Titel :

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


    Beteiligte:

    Kongress:

    41st AIAA Aerospace Sciences Meeting and Exhibit ; 2003 ; Reno, NV, United States


    Erscheinungsdatum :

    2003-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :