Laminar Separation, Transition, and Turbulent Reattachment near the Leading Edge of Airfoils
Laminar Separation, Transition, and Turbulent Reattachment near the Leading Edge of Airfoils
复制标题
机翼前缘附近的层流分离、转变和湍流重新附着
DOI：
10.2514/3.50815
复制
发表时间：
1980
期刊：
影响因子：
2.5
通讯作者：
T. Mueller
中科院分区：
文献类型：
--
作者：
A. Arena;T. Mueller
利用低湍流度、低速烟风洞研究了圆柱形等厚度翼型模型前缘附近的层流分离、转捩和湍流再附。分离、转捩和再附着的位置是从烟流照片和表面油流技术中获得的，弦雷诺数约为150，000至470，000。这些可视数据与静压分布相结合，描述了攻角、襟翼偏转角和弦雷诺数对分离泡特性的影响。关于气泡的层流和湍流部分的长度的数据与短气泡的经验预测方法一致。
The laminar separation, transition, and turbulent reattachment near the leading edge of a cylindrical noseconstant thickness airfoil model were investigated using a low-turbulence, low-speed smoke wind tunnel. The locations of separation, transition, and reattachment were obtained from smoke flow photographs and surface oil flow techniques for chord Reynolds numbers from about 150,000 to 470,000. These visual data combined with static pressure distributions delineate the effects of angle of attack, flap deflection angle, and chord Reynolds number on the separation bubble characteristics. The data concerning the length of the laminar and turbulent portions of the bubble agree with the empirical prediction methods for short bubbles.