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Leading edge sweep effects in generic three-dimensional sidewall compression scramjet inletsA computational and experimental study of generic 3D sidewall compression inlets is conducted to examine the effects of fore and aft leading edge sweep on the internal shock structure. Inlets with leading edge sweeps of +30 deg and -30 deg with sidewall compression angles of 6 deg were tested in the NASA Langley Mach 4 air tunnel at a geometric contraction ratio of 1.87. The principal difference in performance was determined to be in the mass capture. Spillage was identified as having two components: a pressure induced component and a sweep induced component. It was found that while the direction of the leading edge sweep had a large influence on the spillage, the pressure effects were more important.
Document ID
19920045594
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cozart, Aaron B.
(North Carolina State University Raleigh, United States)
Holland, Scott D.
(NASA Langley Research Center Hampton, VA, United States)
Trexler, Carl A.
(NASA Langley Research Center Hampton, VA, United States)
Perkins, John N.
(North Carolina State University Raleigh, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-0674
Accession Number
92A28218
Funding Number(s)
CONTRACT_GRANT: NGT-70161
Distribution Limits
Public
Copyright
Other

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