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本文根据小扰动渐近展开的内外解衔接法,对亚音速全机侧滑问题,用源(汇)、偶极子分布代表机身,涡格分布代表升力面;並对翼-身、翼-尾干扰提出了小扰动处理法。通过算例表明,本文提供的方法是可行的。
In this paper, based on the internal and external solution of asymptotic expansion of small perturbation, the distribution of source body (voxel) - tail disturbance proposed a small disturbance method. An example shows that the method provided in this paper is feasible.