高速大攻角Re数效应试验与分析

Analysis of high speed Reynolds number effect tests at high angles of attack

采用两个尺度不同的某战斗机模型,在2.4m高速风洞中进行了大攻角Re数效应试验研究。试验攻角范围为0°-70°,基于前机身端部当量直径的ReD=0.42×10^6-2.27×10^6。试验结果表明,Re数对大攻角试验数据影响明显;表面微几何效应、M数同样对大攻角气动特性也有一定影响;模型头部贴＂八＂字形粗糙带可以减弱Re数的影响,却不能获得高Re数下的试验结果。

Using two different scaled fighter models, the Reynolds number effect tests at high angles of attack were completed in FL-26 wind tunnel. The angles of attack ranged from 0° - 70°, and the Reynolds number based on mean diameter of fore-model ranged from 0.42 × 10^6 - 2.27 × 10^6. The results showed that the aerodynamic characteristics at high angles of attack could significantly depend on Reynolds number effect, and also depend on surface micro geometry effect and Mach number effect to some extend. Placing twin strips at fore-model could weaken Reynolds number effect, but could not simulate the test results of high Reynolds number.