The Effect of Bleed on Two-Dimensional Base Flow at Subsonic, Transonic and Low Supersonic Speeds,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1978
- Accession Number
- ADA071362
Entities
People
- N. Pollock