旋成体仿生凹坑表面减阻试验研究  

Experimental study on bionic dimpled surfaces of bodies of revolution for drag reduction

作　　者：张成春[1,2] 任露泉[2] 刘庆平[2] 冯家波[3] 秦永明[3] 

机构地区：[1]清华大学汽车工程系,汽车安全与节能国家重点实验室,北京100084 [2]吉林大学地面机械仿生技术教育部重点实验室,吉林长春131022 [3]航天空气动力技术研究院,北京100074

出　　处：《空气动力学学报》2008年第1期79-84,共6页Acta Aerodynamica Sinica

基　　金：科技部国际合作重点项目(2005DFA00850);“863”国家计划项目(2003AA305080);博士点基金项目(20050183064);吉林省科技发展项目(国际合作)(20040703-1)

摘　　要：基于非光滑表面减阻的仿生学理论,通过凹坑表面控制超声速旋成体附壁区的边界层结构来减小旋成体的阻力。利用3因素5水平的二次旋转设计,对排列在旋成体后部的仿生凹坑表面参数进行优化。Ma数为2.51,基于旋成体最大直径的雷诺数为1.9×106的风洞试验表明,旋成体后部的凹坑表面最大可减小旋成体4.98%的粘性前部阻力以及2.69%的底部阻力,总阻力最大可减小2.98%。通过二次旋转设计得到关于凹坑直径、深度以及凹坑轴向间距三个因素的二次回归方程,利用此方程得到的最优凹坑表面减少总阻力4.4%。In view of the bionics theory that unsmoothed surface can reduce the viscous drag of a body, the drag reduction using dimpled surfaces was investigated for the bodies of revolution by controlling the surface boundary layer structure. A quadratic rotatable design with 3 factors and 5 levels for each factor was used to optimize the parameters of the dimpled surfaces. The wind tunnel tests with Ma = 2.51 and the Reynolds number 1.9×10^6 based on the maximal diameter of the model indicate that the dimples on the rearward configuration can reduce the viscous forebody drag by 4.98 %, the base drag by 2.69 %, and the total drag by 2.98 % respectively. With the dimpled surface obtained by the quadratic regression equation of the diameter, the depth of the dimples and the space between adjacent dimples in the axial direction, the total drag can be reduced by 4.4%.

关 键 词：工程仿生学 减阻 边界层控制 风洞试验 二次旋转设计 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]