Accession Number : ADA298056

Title :   An Experimental Investigation of Cavity Aeroacoustics in High Speed Flows.

Descriptive Note : Final rept.,

Corporate Author : TENNESSEE UNIV SPACE INST TULLAHOMA

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

PDF Url : ADA298056

Report Date : MAY 1995

Pagination or Media Count : 71

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 to 17 millions per foot. Measurements were performed for a number of injection distributions. The large amplitude oscillations measured without mass injection was successfully and totally eliminated with proper mass injection.

Descriptors :   *FLOW NOISE, *BOMB BAYS, *AERODYNAMIC NOISE, SHEAR PROPERTIES, INTERACTIONS, LAYERS, HIGH VELOCITY, TURBULENT BOUNDARY LAYER, CAVITIES, MASS FLOW, FLOW FIELDS, WIND TUNNEL TESTS, MACH NUMBER, AMPLITUDE, OSCILLATION, REYNOLDS NUMBER.

Subject Categories : Acoustics
      Military Aircraft Operations

Distribution Statement : APPROVED FOR PUBLIC RELEASE