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Reynolds Number and Leading-Edge Bluntness Effects on 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 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.
Document ID
20020016863
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Luckring, J. M.
(NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2002
Subject Category
Aerodynamics
Report/Patent Number
AIAA Paper 2002-0419
Meeting Information
Meeting: 40th AIAA Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 14, 2002
End Date: January 17, 2002
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.
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