2.4m跨声速风洞Re数模拟能力及其应用  

Reynolds number variation capability and applications of 2.4m transonic wind tunnel

作　　者：钟世东[1] 吴军强[1] 魏志[1] 王瑞波[1] 杨可[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》2008年第4期76-79,共4页Journal of Experiments in Fluid Mechanics

摘　　要：Re数对飞行器气动特性的影响十分复杂,基于风洞试验的Re数效应预测很大程度上依赖于风洞的变Re数试验能力。综述了2.4m跨声速风洞的Re数模拟能力,并给出了某型无人机和某型战斗机在2.4m风洞的变Re数试验结果以及战斗机大迎角气动特性的Re数效应试验结果,表明了2.4m风洞的Re数模拟能力能够较好地预测Re数对飞行器气动特性的影响趋势,大迎角试验时,基于机头端部直径的试验Re数能达到超临界范围。Reynolds number has a complicated effect on aerodynamic character of aircrafts. Predicting Reynolds number effects based on test data is highly depended on Reynolds number variation capability of facilities. This paper introduces the 2.4m transonic wind tunnel＇ s Reynolds number variation capability. Some resuits are presented including tests for a pilotless aircraft and a fighter plane that were implemented in 2.4m wind tunnel. Reynolds number effects at high angle of attack of a fighter plane are also given. The results show that 2.4m transonic wind tunnel＇s Reynolds number variation capability can satisfy the needs to predict Reynolds number effects. Reynolds number at high angle of attack for a fighter plane based on diameter of aircraft prow reaches supercritical range.

关 键 词：跨声速风洞 Re数模拟能力 风洞试验 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]