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Computer simulation of shock wave boundary layer interactionDevelopment of a boundary layer correction for an analysis program previously used by Bauer et al. (1972) to study two-dimensional flow past transonic airfoils at off-design conditions where shocks which interact with the boundary layer appear. Using a method which combines conformal mapping with a finite-difference scheme due to Murman and Cole (1971), an analysis is made of the interaction between shock waves on a supercritical wing section and a turbulent boundary layer, assuming that the shocks are weak and that separation is insignificant. It is shown that relatively simple shock wave/boundary layer interactions of the kind envisioned in this study can be treated by determining the displacement thickness iteratively together with the flow and altering the profile accordingly. It is concluded that the proposed boundary layer correction appears to furnish an essential improvement in cases where both pronounced aft loading and a large enclosed supersonic region of flow are present.
Document ID
19740041850
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Bauer, F.
Garabedian, P.
(New York University New York, N.Y., United States)
Date Acquired
August 7, 2013
Publication Date
November 1, 1973
Publication Information
Publication: Communications on Pure and Applied Mathematics
Volume: 26
Subject Category
Aerodynamics
Accession Number
74A24600
Funding Number(s)
CONTRACT_GRANT: AT(11-1)-3077
CONTRACT_GRANT: NGR-33-016-167
Distribution Limits
Public
Copyright
Other

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