Flow Control Mechanisms Study over Conical Forebody Using Plasma Duty Cycles
A novel design and placement of a pair of SngleDielectric-Barrier-Discharge (SDH)) plasma actuators near body apex with duty cycle were shown successful by Liu et al. (2008). To study the mechanisms of flow control on slender conical cone at high angles of attack using plasma actuators, unsteady pressure is investigated in the presented paper. The tests are conducted in a low-speed wind tunnel which has a 3.0 m×1.6 m cross section. The test angle of attack is 458. The Reynolds number based on the cone base diameter is 5 × 104. Two long strips of SDBD plasma-actuators are installed symmetrically near the apex of the cone. The duty cycles are achieved at a frequency of 10 Hz. The test results indicate that the variation of the phaselocked-averaged side force in a period of the duty cycle is a smoothwave curve rather than the square-wave curve. The linearity of the controlled lateral forces and moments with respect to the duty cycle is improved over previous studies because of the improved design of the actuators.
slender body asymmetric vortices high Angle of Attack Aerodynamics plasma active flow control
Meng Xuanshi Wang Jianlei Zhao Zijie Liu Feng Luo Shijun
National Key Laboratory of Science and Technology on Aerodynamic Design and Research,Northwestern Po The Department of Mechanical and Aerospace Engineering,University of California, CA 92697-3975,Ameri
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
195-198
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）