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- W2084314533 abstract "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" @default.
- W2084314533 created "2016-06-24" @default.
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- W2084314533 date "2004-01-05" @default.
- W2084314533 modified "2023-09-25" @default.
- W2084314533 title "Compressibility and Leading-Edge Bluntness Effects for a 65o Delta Wing" @default.
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- W2084314533 doi "https://doi.org/10.2514/6.2004-765" @default.
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