Accession Number:

ADA196094

Title:

Aeroacoustic Effects of Body Blockage in Cavity Flow

Descriptive Note:

Final rept. Sep 1986-Sep 1987

Corporate Author:

AIR FORCE ARMAMENT LAB EGLIN AFB FL

Report Date:

1987-10-19

Pagination or Media Count:

10.0

Abstract:

In order to study the effects of unsteady dynamic and steady static pressure waves in a cavity at subsonic Mach numbers through transonic Mach numbers, an experimental test program, using a splitter plate and a generic cavity, was conducted. Since most cavities associated with air vehicles house sensors, equipment, or armament, ogive cylinder models were also fabricated and tested inside the cavity to determine their effect on the static and dynamic pressure measurements on the cavity ceiling and walls. The intent of the experiment was to document the effects on steady and unsteady pressures by varying parameters such as the Mach number, cavity dimensions, blockage, and cavity angle of attack. These results will provide engineers with a technology base to aid in the formulation of design requirements and preliminary designs for future air vehicles requiring external cavities. The value of this research is that it provides a more detailed and extensive data base for engineers to utilize during early stages of air vehicle design requiring the utilization of internal design requiring the utilization of internal cavities. Additional tests are currently being planned which will extend this technology data base even further to include aeroacoustic suppressors, cavity doors, and supersonic Mach number effects.

Subject Categories:

  • Aerodynamics
  • Acoustics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE