Accession Number : AD0862496

Title :   An Experimental Investigation of Shock Wave -- Boundary Layer Interaction Dynamics.

Descriptive Note : Final rept. Dec 67-15 Apr 69,

Corporate Author : TENNESSEE UNIV SPACE INST TULLAHOMA

Personal Author(s) : Braun, Gerhard W. ; Snyder, William T.

Report Date : OCT 1969

Pagination or Media Count : 121

Abstract : Wind tunnel tests were performed which simulated the flow pulsations which are sometimes produced in engine inlets by shock-boundary layer interaction. Shock Mach numbers from 1.2 to 1.4 were used and the boundary layer was influenced by air bleeding in or sucking off. The flow was observed by shodowgraph and static and total pressures were measured by means of low frequency and high frequency response instruments. Static wall pressures, boundary layer pressure profiles, and total pressure distributions across several tunnel cross sections were plotted. The data were analyzed with respect to their rms value and power spectral density. A literature survey and an analytical investigation of the pulsations in a diffuser with nonviscous flow are included. (Author)

Descriptors :   *SHOCK WAVES), (*SUPERSONIC AIRCRAFT, JET ENGINE INLETS), (*JET ENGINE INLETS, SUPERSONIC CHARACTERISTICS), (*BOUNDARY LAYER, INTERACTIONS, DUCT INLETS, PRESSURE, DISTRIBUTION, FLOW SEPARATION, POWER SPECTRA, SUPERSONIC DIFFUSERS.

Subject Categories : Aircraft
      Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE