尾撑大迎角试验技术研究  

Study on high angle of attack test technique of rear sting supports

作　　者：祝明红[1] 王勋年[1] 张钧[1] 孙传宝[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2006年第2期25-29,35,共6页Journal of Experiments in Fluid Mechanics

摘　　要：介绍了在4m×3m低速风洞利用尾撑方式进行某飞机模型低速大迎角风洞试验的情况,在0°≤α≤90°的试验迎角范围内,对分两段完成的飞机低速大迎角风洞试验存在的数据衔接性问题做了简要的分析。研究表明,分段进行飞机低速大迎角试验结果的精度能够满足试验要求,但是不同预弯角度的尾撑支杆在重叠的试验迎角时试验结果存在一小量数据台阶,说明其各自的支架干扰不同,对各自的支架干扰还需作进一步的研究。The high angle of attack experiments were carried out using rear sting speed wind tunnel. The test was divided into two ranges. In one range α is - 4° - 49°, and in the other range a is 46° - 91°. The test data have an error for the two ranges at 46° ≤ α ≤ 49°, which is an overlap area within the test attack angle. The continuity of the test results in the joint test attack angle area is analyzed. It is shown that this error must come from the various stings in the overlap area of attack angle, so the interference of various stings must be studied further.

关 键 词：尾撑 试验技术 大迎角 

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]