Accession Number:

AD0642435

Title:

INVESTIGATION OF THE PRESSURE DISTRIBUTION ON A BLUNT-FIN BLUNT-PLATE COMBINATION AT A MACH NUMBER OF 11.26,

Descriptive Note:

Corporate Author:

AEROSPACE RESEARCH LABS OFFICE OF AEROSPACE RESEARCH WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

Report Date:

1966-07-01

Pagination or Media Count:

198.0

Abstract:

The purpose of the investigation was to determine the pressure field on a blunt flat plate in the vicinity of the junction of a three-dimensional fin-plate combination. For the investigation to cover a broad spectrum of configurations, different plate angles of attack, various fin yaw angles, and two fin yaw angles were employed. The investigation was divided into two parts. In the first part, the experimental pressures on a blunt flat plate were measured with and without a blunt fin mounted between the centerline and the trailing edge of the flat plate. In the investigation the plate had an angle of attack of zero or 10 degrees compression. The fin-plate pressure data were obtained for a 45 degree swept and unswept blunt fin at zero and 10 degree fin yaw angle. Both the plate and the fin had hemicylindrical leading and trailing edges. All of the data were taken at a Mach number of 11.26 and Re sub d of 6300. The seond part of the investigation consisted of the development of an analytical method of predicting Mach numbers and flat plate pressures for the same configuration. The analytical method was based on a simplified Lees and Reeves solution of the boundary layer-shock interaction problem extended to three dimensions by use of a two-dimensional strip analysis. Author

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE