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.
Reynolds Number and Leading-Edge Bluntness Effects on a 65 deg Delta Wing
40th AIAA Aerospace Sciences Meeting and Exhibit ; 2002 ; Reno, NV, United States
2002-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Transonic Reynolds Number and Leading-Edge Bluntness Effects on a 65^o Delta Wing
British Library Conference Proceedings | 2003
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