Flow Control on Elliptic Airfoil Using Synthetic Jets
In the present work, the aerodynamic characteristics of elliptic airfoil of 12％ thickness were numerically investigated based on Reynolds-averaged Navier-Stokes equations and transition SST model for Reynolds number 8. 0× 105. And also, the numerical simulation of a synthetic jet actuator which is well-known zero-net-mass active flow control actuator and located at x/c = 0.00025 was performed to control the massive separation around the leading edge of elliptic airfoil. Three cases of non-dimensional frequencies were researched at the angle of attack of 12 degrees. The size of vortex induced by synthetic jet gets smaller as the jet frequency increases. Comparing the location of synthetic jets between x/c = 0.00025 (around the leading edge) and x/c = 0.9 (near the separation) reveals that the synthetic jet near leading edge interacts with the external flow and induces closed recirculation flow region, but the synthetic jet at 0.9c (near trailing edge) induces very small and weak vortex which is quickly decayed for weak intensity.
active flow controls elliptic airfoil synthetic jet
Kim Sunghoon Kim Cheolwan Lee Daesung
Aircraft System Engineering, University of Science and Technology, Daejeon 305-333, Rep of Korea Aerodynamics&Structures Department Korea Aerospace Research Institute, Daejeon 305-333, Rep of Korea Aeronautics R&D Head Office,Korea Aerospace Research Institute, Daejeon 305-333, Rep of Korea
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
219-222
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）