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Experimental Investigation of the Flow about a 65 deg Delta Wing in the NASA Langley National Transonic FacilityAn experimental investigation for the flow about a 65 deg. delta wing has been conducted in the NASA Langley National Transonic Facility (NTF). The tests were conducted at Reynolds numbers, based on the mean aerodynamic chord, ranging from 6 million to 120 million and at Mach numbers ranging from 0.4 to 0.9. The model incorporated four different leading-edge bluntness values. The data include detailed static surfacepressure distributions as well as normal-force and pitching-moment coefficients. The test program was designed to quantify the effects of Mach number, Reynolds number, and leading-edge bluntness on the onset and progression of leading-edge vortex separation.
Document ID
20100009731
Acquisition Source
Langley Research Center
Document Type
Other
Authors
Luckring, James M.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 25, 2013
Publication Date
October 1, 2009
Publication Information
Publication: Vortex Breakdown Over Slender Delta Wings
Subject Category
Aerodynamics
Distribution Limits
Public
Copyright
Other
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