Accession Number:

ADA026526

Title:

Investigation of Small Surface Protuberances Up-Stream of Turbulent Boundary Layer Separation Produced by a Skewed Shock at Mach 3.

Descriptive Note:

Interim rept. Jan-Feb 76,

Corporate Author:

AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

Report Date:

1976-05-01

Pagination or Media Count:

19.0

Abstract:

Tests were undertaken to determine the effect, if any, of a row of small sub-boundary layer-sized cylinders on a region of three-dimensional turbulent boundary layer separation produced by a skewed shock wave at a Mach number of 3. Surface oil flows and pressures showed no influence of the row of cylinders on the region of separation. Author

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE