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

摘要

The research presented in this report has been directed to study the effects ofmass 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).