旋成体非对称涡Re数效应的分区性态研究  

The study of zonal behaviors of Reynolds number effects on asymmetric vortices over slender body

作　　者：邓学蓥[1] 柏楠[1] 马宝锋[1] 陈莹[1] 王延奎[1] 

机构地区：[1]北京航空航天大学流体力学教育部重点实验室,北京100083

出　　处：《空气动力学学报》2007年第B12期48-52,共5页Acta Aerodynamica Sinica

基　　金：国家自然科学基金重点资助项目（10432020）和国防预研基金重点资助项目（9140A13020106HK0111）

摘　　要：本文利用长细比为3．0的尖拱形头部，其后为圆柱段，整体长细比为6．0的旋成体模型在北京航空航天大学流体力学研究所D4低速风洞和西北工业大学翼型、叶栅重点实验室NF-3风洞中进行了大攻角非对称涡绕流的胁D数效应及其分区性态的实验研究，其胁。数变化范围是0．6×10^5-13．3×10^5。文内首先研究和详细讨论了不同胁。数下非对称涡性态的分区特性；其次，为了研究湍流分离下过临界非对称涡流动的性态及其忍。数效应，本文发展了利用粘贴转捩带或转捩丝的人工转捩实验技术；在此基础上详细研究了过临界胁。数下非对称涡流动的性态包括流动的确定性、头部扰动周向位置变化引起非对称涡的演化规律以及过临界区的胁数影响规律。In order to study the Reynolds number effects with zonal behaviors on the asymmetric vortex flow over slender body, the experimental investigations were carried out in D-4 Low Speed wind tunnel of BUAA and the NF-3 wind tunnel of Northwest Polytechnic University （NPU） on a 3D pointed tangent ogive/cylinder model with fineness ratio 6 in Reynolds numbers range 0.6 × 105-13.3 × 105 at high angle of attack. At first, the zonal behaviors of Reynolds number effects on asymmetric vortices over slender body were discussed in detail and a new inception regime with down- and up-ritical Reynolds number is introduced, in which the vortex pattern with subcritical Reynolds number regime on one side of body and the vortex pattern with critical Reynolds number regime on the other side. Then, in order to expand the Reynolds num- ber of running wind tunnel to the post-critical range in the conventional wind tunnel, an artificial transition technique with grit strips or metal thread was developed. Based on this technique, the behaviors of asymmetric vortices at post-critical regime was studied which include its deterministic feature, the evolution and development of asymmetric vortices with the perturbation on the model nose and the Reynolds number effect in the post-critical Reynolds number range.

关 键 词：非对称涡 Re数效应 人工转捩 大迎角空气动力学 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]