Accession Number : ADA290764
Title : Experimental Research on Crossing Shock Wave Boundary Layer Interactions.
Descriptive Note : Final technical rept. 1 Apr 91-30 Sep 94,
Corporate Author : PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF MECHANICAL ENGINEERING
Personal Author(s) : Settles, G. S. ; Garrison, T. J.
PDF Url : ADA290764
Report Date : 30 OCT 1994
Pagination or Media Count : 42
Abstract : An experimental research effort of the Penn State Gas Dynamics Laboratory on the subject of crossing shock wave boundary layer interactions is reported. This three year study was supported by AFOSR Grant 89-0315. A variety of experimental techniques were employed to study the above phenomena including planar laser scattering flowfield visualization, kerosene lampblack surface flow visualization, laser-interferometer skin friction surveys, wall static pressure measurements, and flowfield five-hole probe surveys. For a model configuration producing two intersecting shock waves, measurements were made for a range of oblique shock strengths at freestream Mach numbers of 3.0 and 3.85. Additionally, measurements were made at Mach 3.85 for a configuration producing three intersecting waves. The combined experimental dataset was used to formulate the first detailed flowfield models of the crossing-shock and triple-shock wave/boundary layer interactions. The structure of these interactions was found to be similar over a broad range of interaction strengths and is dominated by a large, separated, viscous flow region. (AN)
Descriptors : *SHOCK WAVES, *TURBULENT BOUNDARY LAYER, *FLOW FIELDS, PROBES, EXPERIMENTAL DATA, COMPARISON, COMPUTATIONAL FLUID DYNAMICS, FLOW VISUALIZATION, GAS DYNAMICS, COMPRESSIBLE FLOW, MACH NUMBER, INVISCID FLOW, FREE STREAM, VISCOUS FLOW, STATIC PRESSURE, GAS SURFACE INTERACTIONS, SKIN FRICTION, SUPERSONIC WIND TUNNELS, INTERFEROMETERS, THREE DIMENSIONAL FLOW.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE