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本文应用运动涡有限基本解方法求得亚声速机翼在运动突风作用下非定常气动力的数值解。对于不同平面形状的机翼进行了计算。计算结果表明,该方法解类似的问题是有效的。
In this paper, the finite basic solution method of motion vortex is used to obtain the numerical solution of unsteady aerodynamics of subsonic aerodynamic wing under the action of motion gust. For different plane shape of the wings were calculated. The calculation results show that this method is effective for solving similar problems.