基于近似边界条件的翼型跨声速颤振数值模拟研究

Numerical Simulation of Transonic Flutter for Airfoil Using Approximate Boundary Conditions

采用近似边界条件对二维翼型的跨声速颤振进行了数值模拟。计算网格采用静止的笛卡儿网格,通过薄翼和机翼小变形假设,使用一阶近似边界条件求解欧拉方程;由于文中方法在计算过程中不需要重新生成网格,节省了大量的时间。计算了Isogai机翼模型的颤振边界,与参考文献的计算结果吻合良好,证明了基于近似边界条件的跨声速颤振数值模拟方法的高效性和准确性。

Numerical simulation of aircraft＇s flutter is rather expensive and time-consuming. In order to save expense and calculating time, we apply first-order approximate conditions to solve the unsteady transonic Euler equations coupled with aeroelastic equations. Assuming that the airfoil is thin and undergoes small deformation, we implement wall boundary conditions on non-moving mean wall positions. Then the first-order approximate equation of momentum is obtained by using Taylor expansion. Unsteady transonic Euler equations are solved on stationary Cartesian grids. Both the result of unsteady transonic calculation for NACA64A010 airfoil and the result of aeroelastic calculation for ISOGAI wing model are in good agreement with related references, preliminarily indicating that the first-order approximate conditions are effective for aeroelastic simulation.