细长体大迎角压缩性效应试验分析  

Analysis of compressibility effect tests on ogive slender body at high angles of attack

作　　者：贺中[1] 范召林[1] 王元靖[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：《空气动力学学报》2010年第3期332-335,357,共5页Acta Aerodynamica Sinica

摘　　要：采用尖拱细长体模型,在高速风洞中完成了压缩性对大迎角非对称流动影响的试验研究。试验迎角范围为10°～50°,M数范围为0.4～1.2。试验结果表明:压缩性对非对称流动的产生和发展过程不产生本质影响,但影响非对称的强弱和发展速度;当横流Mc<0.4时,流动非对称性随M数增加而增加,当Mc>0.4时,流动非对称性随M数增加而减弱;Re数和压缩性均对非对称涡流动产生明显影响。Using tangent-ogive slender body, the tests were completed in high speed wind tunnel to investigate the effects of compressibility on the asymmetric vortex flow at high angles of attack. The angles of attack ranged from 10° to 50°, and the Mach number ranged from 0.4 to 1.2. The results showed that the compressibility couldn＇t essentially affect the appearance and development course of asymmetric flow but the strength and development speed, and Reynolds number and compressibility affect asymmetric vortex flow together. Jt was observed that the asymmetry would be increased with Mach number increasing when Mc〈 0.4, and reduced with Maeh number decreasing when Mc0〉. 4.

关 键 词：大迎角空气动力学 压缩性 非对称涡 风洞试验 

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]