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Flowfield in the plane of symmetry below a delta wingThe flowfield in the plane of symmetry of a thin lifting delta wing with supersonic leading edges is examined for wings with apex angles that are comparable to the Mach angle, as well as for the limiting case of a straight leading edge. For these two cases, a simplified treatment of the interaction between the plane expansion wave emanating from the trailing edge and the three-dimensional bow shock is presented. In the region unaffected by the wing tips, the shock decays inversely with distance from the wing.
Document ID
19760048214
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Cramer, M. S.
(Cornell Univ. Ithaca, NY, United States)
George, A. R.
(Cornell Univ. Ithaca, NY, United States)
Seebass, A. R.
(Cornell University Ithaca, N.Y., United States)
Date Acquired
August 8, 2013
Publication Date
February 1, 1976
Publication Information
Publication: AIAA Journal
Volume: 14
Subject Category
Aerodynamics
Accession Number
76A31180
Funding Number(s)
CONTRACT_GRANT: NGR-33-010-057
CONTRACT_GRANT: NGR-33-010-203
Distribution Limits
Public
Copyright
Other

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