超临界翼型跨声速激波振荡数值模拟  

Numerical simulation of transonic shock oscillations on a supercritical airfoil

作　　者：魏志[1] 陶洋[2] 王红彪[1] 

机构地区：[1]中国科学技术大学工程科学学院近代力学系,合肥230026 [2]中国空气动力研究与发展中心高速空气动力研究所,四川绵阳621000

出　　处：《航空动力学报》2011年第7期1615-1620,共6页Journal of Aerospace Power

基　　金：国家自然科学基金(10972233)

摘　　要：应用DES(detached eddy simulation)方法研究了SC(2)-0714超临界翼型跨声速自维持激波振荡现象.使用的DES方法预测了激波在翼型上表面的周期性运动,分析了雷诺数对激波运动的减缩频率、平均激波位置、脉动压力系数等非定常特性的影响.结果表明:雷诺数对激波振荡运动特性的影响呈非线性关系;而雷诺数为6×106时的激波振荡运动特性与雷诺数分别为15×106及30×106时的特性存在明显差异.Detached eddy simulation （DES） method was applied to study the self-sustained shock oscillations phenomenon of SC（2）-0714 supercritical airfoil in this paper. The periodic shock motion on the upper surface of the airfoil was predicted using the two-dimensional DES method in present calculation. The effects of Reynolds number （Re） on the reduced frequency of the shock motion, mean shock position and coefficients of fluctuation pressures were also studied in the paper. The results show that Reynolds number has a nonlinear influence on shock oscillation motion character. Compared with Re=15 × 10^6 and Re=30 × 10^6 flow condition, the shock oscillation character in case of Re=6×10^ 8 condition is obviously different.

关 键 词：超临界翼型 跨声速流动 激波 自维持运动 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]