Accession Number:

ADA134579

Title:

Mach 0.6 to 3.0 Flows over Rectangular Cavities

Descriptive Note:

Final rept. Jun 1978-Jun 1980

Corporate Author:

AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH

Report Date:

1983-05-01

Pagination or Media Count:

297.0

Abstract:

Internal weapons carriage in high performance aircraft is often adversely affected by the severe aeroacoustic environment produced with the weapons bay doors open. To obtain a better understanding of this fluid dynamic problem, basic static and oscillatory pressure data were obtained for Mach 0.6 to 3.0 flows over shallow rectangular cavities in a generic flat plate model. Cavity length to depth ratios were varied from approximately 5 to 10. Static pressure data characteristic of both open and closed cavity flows were obtained. An improved Rossiter method is presented that satisfactorily predicts the possible frequency modes within the cavity. Highest fluctuating pressure occurs on the aft bulkhead, peaking near Mach 1.5 for the conditions tested. Aeroacoustic levels are substantially reduced by installing suppression fences spoilers at subsonic and low supersonic conditions. Acoustic levels generally drop rapidly above Mach 1.5. Author

Subject Categories:

  • Aerodynamics
  • Aircraft
  • Acoustics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE