某型号飞机简化模型大攻角流态初步研究  

Experimental Study on the Flow Patterns of a Simplified Aircraft Model at High Angles of Attack

作　　者：王晋军[1] 薛启智[1] 白涛[1] 冯亚南[1] 

机构地区：[1]北京航空航天大学飞行器设计与应用力学系

出　　处：《北京航空航天大学学报》2000年第2期171-173,共3页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家部委基金资助项目

摘　　要：在水洞中应用染色液流动显示技术对某型号飞机简化模型机头流动状况随攻角和来流速度的演化进行了观测和分析 .实验结果表明 ,在本实验条件下 ,对于不同的来流速度或雷诺数 ,每种流动现象所对应的攻角确实发生了变化 ,说明雷诺数的影响确实存在 ;另外 ,对自由转捩条件下 ,俯仰力矩曲线在α =35°～ 70°之间很分散的风洞实验结果进行了初步的解释 :α =35°基本上对应于边条涡非对称破裂的开始 ;而α =70°则对应于机头迎风面流动向前。The dye injection flow visualization technique has been used to study the changes of flow patterns for a simplified aircraft model with the variation of angles of attack and the incoming flow velocity in a water tunnel. In this experiment, the changes of flow patterns do not have essential difference at several incoming flow velocities, but the variation of the relevant angles of attack occurs indeed, which means that there exists the Re dependence. Moreover, for the scatter of the experimental pitch up moment curve in the case of natural transition, the explanation has been made. α =35° corresponds the start of asymmetric breakdown of the strake vortex and α =70° is the critical point of the flow forth and back in the up wind side of the nose.

关 键 词：涡旋流动 流动显示 大攻角 简化飞机模型 

分 类 号：V211.24[航空宇航科学与技术—航空宇航推进理论与工程] V211.4