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Compressibility and Leading-Edge Bluntness Effects for a 65 Deg Delta WingA 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
Document ID
20040008868
Acquisition Source
Langley Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Luckring, J. M.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 21, 2013
Publication Date
January 1, 2004
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA Paper 2004-0765
Meeting Information
Meeting: 42nd AIAA Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 5, 2004
End Date: January 8, 2004
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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