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RESEARCH PAPERS

Compressible Boundary Layer-Inviscid Flow Interactions in Entrance Region of Internal Flows

[+] Author and Article Information
V. D. Blankenship

Mark 18 Reentry System, Aerospace Corporation, San Bernardino, Calif.

P. M. Chung

University of Illinois, Chicago, Ill.

J. Heat Transfer 89(4), 281-288 (Nov 01, 1967) (8 pages) doi:10.1115/1.3614386 History: Received July 10, 1966; Revised March 27, 1967; Online August 25, 2011

Abstract

The coupling between the inviscid flow and the compressible boundary layer in the developing entrance region for internal flows is analyzed by solving the particular inviscid flow-boundary layer interaction problem. The interaction problem is solved by postulating certain series forms of solutions for the inviscid region and the boundary layer. The boundary-layer equations and inviscid-flow equations are perturbed to third order and each generated equation is solved numerically. In order to preserve the universality of each of the perturbed boundary-layer equations, the perturbation parameter is described by an integral equation which is also solved in series form. The final results describing the interaction problem are then constructed for any given conditions by forming the three series to a consistent order of magnitude. This technique of coordinate perturbation is generalized to show how it may be applied to the entrance regions of pipe flows, including mass injection or suction, and also to the laminar boundary layers in shock tube flows. It demonstrates analytically the manner in which the boundary layer and inviscid flow interact and create a streamwise pressure gradient. In particular, the interaction problem which occurs in shock tube flows is solved in detail by the use of this generalized method, as an example.

Copyright © 1967 by ASME
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