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
Compressibility and Leading-Edge Bluntness Effects for a 65 Deg Delta Wing
42nd AIAA Aerospace Sciences Meeting and Exhibit ; 2004 ; Reno, NV, United States
2004-01-01
Preprint
Keine Angabe
Englisch
Compressibility and Leading-Edge Bluntness Effects for a 65^o Delta Wing
British Library Conference Proceedings | 2004
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