Vortex Breakdown on Slender Flat-plate Delta Wing with Dorsal Fin
A 2D Particle Image Velocimetry (PIV) study is performed on a flat-plate delta wing of 82. 58sweep angle and combinations of the identical delta wing with low dorsal fins. The test is conducted at a lowspeed wind tunnel at 358 angle of attack and zero sideslip. The PIV technique is used to visualize and measure the distributions of the vorticity component normal to the cross-flow plane at 60％ wing root chord. The same test is performed on an identical delta wing model but with a flat plate dorsal fin mounted vertically in the incidence plane of the wing. Two fin heights are tested,the ratios of the local fin height to the local wing semi-span are 0. 3 and 0. 6 respectively. The PIV results indicate that the vortex pair is symmetric and steady over the wing, but it occurs vortex breakdown periodically when adding the low dorsal fin. The results provide for the first visualization measurements evidence of the validity of the vortex stability theory of Cai, Liu, and Luo (J. Fluid Mech., 2003, 480:65—94) and depict the flow behavior after the onset of the vortex instability.
unsteady vortex breakdown, vortex stability high angle of attack fin slender body flat-plate delta wing
Meng Xuanshi Cai Jinsheng Qiao Zhide Luo Shijun Liu Feng
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
207-210
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）