Investigation of Hypersonic Inlet Shock-Wave Boundary Layer Interaction: Part II - Continuous Flow Test and Analyses

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Report Number: AFFDL TR 65-36
Author(s): Brown, David L., Hoelmer, Werner, Kutschenreuter, Paul H., Jr.
Corporate Author(s): General Electric Company
Laboratory: Air Force Flight Dynamics Laboratory
Pages: 272
Contract: AF 33(657)-11747
DoD Project: 651-E
Identifier: AD0636981

The computational procedure developed in Phase I for estimating laminar boundary layer properties through impinging shock induced laminar boundary layer interactions was modified to account for entropy change of the inviscid streamlines in that isentropic assumptions were used in the initial formulation. Perturbation studies on the effects of wall shear on interaction length have identified the importance of the profile shape factor in such calculations. A Users' Manual for the laminar computational program is contained. Three incident shock models were designed for use in the experimental program conducted in the Ames 3.5 Foot Hypersonic Tunnel. Aided by analysis of the experimental data, a simplified flow model was formulated for the case of a two-dimensional turbulent boundary layer incident shock interaction.

Provenance: Lockheed Martin Missiles & Fire Control

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