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本文用非线性涡格法计算了复杂机翼大攻角分离流定常、非定常气动力,详细地研究了影响该方法的几个主要参数如:前缘分离涡的起点位置,离体涡位置迭代过程中施加的δ松驰因子、计算中须考虑的离体涡长度等等。对于出现部份前缘分离的带边条的机翼,用其非定常的涡格法处理了这一情况,并通过压缩性修正,使方法能计算亚音速大攻角定常气动力。大量算例结果表明本文所得的结果与实验值是一致的。
In this paper, the non-linear eddy-current method is used to calculate the steady and unsteady aerodynamic forces in the separation of large aerogels of complex airfoils. The main parameters influencing this method are studied in detail, such as the starting position of the front vortex, the extrinsic vortex position The δ relaxation factor applied during the iteration, the extrinsic eddy length to be considered in the calculation, and so on. For the edge-separated wing with partial leading edges, this case is dealt with by its unsteady vortex lattice method, and by compressibility correction, the method can calculate the constant aerodynamic force at high subsonic angles of attack. A large number of example results show that the results obtained in this paper are consistent with the experimental values.