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Analysis of the interaction of a weak normal shock wave with a turbulent boundary layerThe method of matched asymptotic expansions is used to analyze the interaction of a normal shock wave with an unseparated turbulent boundary layer on a flat surface at transonic speeds. The theory leads to a three-layer description of the interaction in the double limit of Reynolds number approaching infinity and Mach number approaching unity. The interaction involves an outer, inviscid rotational layer, a constant shear-stress wall layer, and a blending region between them. The pressure distribution is obtained from a numerical solution of the outer-layer equations by a mixed-flow relaxation procedure. An analytic solution for the skin friction is determined from the inner-layer equations. The significance of the mathematical model is discussed with reference to existing experimental data.
Document ID
19740051585
Document Type
Conference Paper
Authors
Melnik, R. E.
Grossman, B. (Grumman Aerospace Corp. Bethpage, N.Y., United States)
Date Acquired
August 7, 2013
Publication Date
June 1, 1974
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 74-598
Meeting Information
Fluid and Plasma Dynamics Conference(Palo Alto, CA)
Funding Number(s)
CONTRACT_GRANT: N00014-71-C-336
CONTRACT_GRANT: NAS1-12426
Distribution Limits
Public
Copyright
Other