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Transonic Reynolds Number and Leading-Edge Bluntness Effects on a 65 deg Delta WingA 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.
Document ID
20040139861
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, 2003
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA Paper 2003-0753
Report Number: AIAA Paper 2003-0753
Meeting Information
Meeting: 41st AIAA Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 6, 2003
End Date: January 9, 2003
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
OTHER: RTA 719-10-40-10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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