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 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.
Transonic Reynolds Number and Leading-Edge Bluntness Effects on a 65 deg Delta Wing
41st AIAA Aerospace Sciences Meeting and Exhibit ; 2003 ; Reno, NV, United States
2003-01-01
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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