Accession Number:

ADA071362

Title:

The Effect of Bleed on Two-Dimensional Base Flow at Subsonic, Transonic and Low Supersonic Speeds,

Descriptive Note:

Corporate Author:

AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA)

Personal Author(s):

Report Date:

1978-11-01

Pagination or Media Count:

39.0

Abstract:

Measurements of the effect of bleed on the base pressure acting on a two-dimensional blunt trailing edge aerofoil are reported and schlieren photographs of the base flow are presented. The tests covered a Mach number range of 0.5 to 1.35 at a base height Reynolds number of approximately 90,000 with turbulent approach boundary layers. The results indicate that small bleed quantities can produce considerably greater base drag reductions at transonic speeds than at subsonic or supersonic speeds. A bleed mass flow coefficient of 0.07 produces a lower base drag than the best practical non-bleed blunt trailing edge geometry through the entire test Mach number range. Author

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE