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现有的跨声速修正面元方法大多难以准确修正非定常压强系数的虚部.结合下洗修正方法和连续核函数展开法(Successive Kernel Expansion Method),发展了一种新的修正方法.计算ONERA M6机翼的非定常气动力,与传统修正方法比较,结果表明该方法具有更高的精度.将改进的非定常气动力用于机翼的跨声速颤振分析,较好地预测了机翼在跨声速区域的非线性颤振特性.
The existing transonic modified face method mostly can not accurately correct the imaginary part of the unsteady pressure coefficient.A new correction method is developed by combining the washdown correction method with the continuous kernel function expansion method.Calculation of ONERA The unsteady aerodynamic force of the M6 wing is compared with the traditional one and the results show that this method has higher accuracy.The improved unsteady aerodynamic force is used for the transonic flutter analysis of the wing, Nonlinear chatter characteristics in transonic region.