An Experimental Study of a Sting-Mounted Circulation Control Wing
Abstract
This wind tunnel study investigated the lift, drag, and pitching moment of a 20% thick, 8.5% camber, partial elliptical cross-section, single blowing slot, 2.325 aspect ratio, rectangular circulation control wing. The AFIT 5-foot wind tunnel was used. Lift and drag were referenced to the wind axis. The Reynolds number was 500,000 for all tests. Angle of attack was varied from -6 to 16 degrees and the effects of pulsed blowing were investigated. Effects of tripping the Coanda jet with a small flow barrier attached spanwise along the Coanda surface were also studied. Results indicate that there is a limit on maximum lift obtainable by increasing circulation. The limit is presumed to be the result of three-dimensional effects. Pulsed blowing has little effect on average lift, but results in violent oscillation of the wing as the sting physically bends under cyclic loading. In certain situations, tripping the Coanda jet may reduce drag without decreasing lift.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1991
- Accession Number
- ADA243912
Entities
People
- Steven J. Lacher
Organizations
- Air Force Institute of Technology