Accession Number : ADA298432

Title :   An Experimental Investigation of Cavity Aeroacoustics in High Speed Flows. Appendix A: Supersonic Data. Appendix B: Subsonic Data.

Descriptive Note : Final rept. 1 Dec 92-28 Feb 95,

Corporate Author : TENNESSEE UNIV SPACE INST TULLAHOMA

Personal Author(s) : Vakili, A. ; Wolfe, Robert ; Nagle, Paul

PDF Url : ADA298432

Report Date : MAY 1995

Pagination or Media Count : 273

Abstract : The research presented in this report has been directed to study the effects of mass injection into the flow upstream of a cavity to understand the weapon bay cavity's flow field and its aeroacoustics. The objective also was to control the development of upstream boundary layer, and therefore, to control the development of the shear layer over the cavity. Control of the shear layer has enabled us to significantly reduce or to fully eliminate the weapons bay's aeroacoustic interactions. This study was performed in a wind tunnel at several nominal Mach numbers between 0.5 to 1.8 and at unit Reynolds numbers up. (AN)

Descriptors :   *SUBSONIC FLOW, *SUPERSONIC FLOW, *CAVITATION, HIGH VELOCITY, BOUNDARY LAYER, MASS FLOW, FLOW FIELDS, WIND TUNNEL TESTS, TABLES(DATA), MACH NUMBER, FLOW NOISE, PRESSURE DISTRIBUTION, DYNAMIC PRESSURE, REYNOLDS NUMBER, SHEAR FLOW, TRAILING EDGES.

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE