The study of Reynolds number effect on the behaviors of axisymmetric vortices flow
In order to study the Reynolds number effects on the behaviors of asymmetric vortexow over slender body the experimental investigations were carried out in D-4 Low Speed WindTunnel of BUAA with pointed tangent ogive/cylinder model with the angle of attack 50_at Reynoldsnumbers 0.1×106￠1.0×106. A new transitional separation pattern in the inception regime wasfound at the Reynolds number 0.2×106, which means the laminar boundary layer separation with theturbulent shear layer reattachment on one side and the laminar boundary layer separation withoutreattachment is still kept on the other side. And the pressure difference _Cp =Cpsep-Cpmincan be selected as criterion to determine the lower-critical and upper-critical Reynolds numbers forinception regime quantitatively. In the post-critical regime it is found from the present study that the asymmetric vortices behaviors are no longer changed with Reynolds numbers. Moreover, theasymmetric vortices ow pattern at bistable state will switch over two cycle. And a close correlationbetween circumferential position of manual micro-perturbation block and the response of asymmetricvortices ow pattern is revealed over the post-critical Reynolds number region.
asymmetric vortex Reynolds number effect high angle of attack aerodynamics slender body
X.Y.Deng N.Bo Y.Chen Y.K.Wang
Ministry-of-Education Key Laboratory of Fluid Mechanics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
国际会议
The Fifth International Conference on Fluid Mechanics(第五届国际流体力学会议)
上海
英文
2007-08-15（万方平台首次上网日期，不代表论文的发表时间）