Akademik Veri Yönetim Sistemi
23rd AIAA Applied Aerodynamics Conference, Toronto, Kanada, 6 - 09 Haziran 2005, cilt.1, ss.410-422
A flow control actuator utilizing steady/pulsating jet of pressurized air was designed and installed in a wind tunnel testing model of elliptic cylinder wing. To test its effectiveness and feasibility for flow separation control, an experimental study was conducted in a subsonic wind tunnel through surface pressure measurements, PIV measurements and flow visualization. The most effective jet slot position was found to be +45° from the chord line toward the upper wing with surface pressure measurements and visualization study. The PIV results showed that both steady and pulsed jets were able to suppress the separation development. However it was found that the pulsed jet was more effective method of separation control for both stationary and oscillating wings. Copyright © 2005 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.