一种考虑攻角影响的超音速翼面颤振分析方法

METHOD TO ANALYSE FLUTTER OF HYPERSONIC WING WITH ATTACK ANGLE

采用活塞理论计算非定常气动力,用新的方法考虑了攻角的影响,和颤振运动方程耦合求解三维翼面的颤振临界条件。分别计算了四种翼型(平板翼,圆弧翼,六边形翼和四边形翼)的颤振临界速度,计算结果和风洞试验数据比较,二者相当一致。

Applying Piston Theory to calculate unsteady aerodynamics, using a new nethod to deal with attack angle, and coupling with flutter motion equation the critical condition of threedimension wings is solved.Critical flutter velocities of four kinds of airfoils (flat airfoil,arc airfoil, hexagon airfoil, and quadrangle airfoil)are calculated, and the results are in good agreement with wind tunnel experiments’ data.