Shock-Stall Flutter of a Two-Dimensional Airfoil
Shock-Stall Flutter of a Two-Dimensional Airfoil
复制标题
二维翼型的冲击失速颤振
DOI：
10.2514/1.9088
复制
发表时间：
2004
期刊：
影响因子：
2.5
通讯作者：
Itsuma Yukimura
中科院分区：
文献类型：
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作者：
M. Yamasaki;K. Isogai;T. Uchida;Itsuma Yukimura
在一个模拟前掠翼典型剖面的单自由度（俯仰）颤振模型的实验中，用一个带高速摄像机的纹影系统观察了由大尺度激波诱导流动分离引起的激波失速颤振。实验结果与计算结果进行了比较，以评估使用可压缩Navier-Stokes方程的数值分析代码。通过实验流动显示和数值模拟得到了翼型的俯仰力矩与攻角的关系以及翼型周围的流态，揭示了激波失速颤振的机理
In an experiment using a single-degree-of-freedom (pitching) flutter model, which simulates the typical section of a forward-swept wing, shock-stall flutter, which is induced by large-scale shock-induced flow separation, has been observed by a schlieren system with a high-speed video camera. The experimental results are compared with computational ones to evaluate the numerical analysis code using the compressible Navier-Stokes equations. The mechanism of the shock-stall flutter is made clear by considering the relations between the pitching moments vs angle of attack and the flow patterns around the airfoil, which are obtained by the experimental flow visualization and the numerical simulation