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本文计算无粘亚音速流中任意平面形状薄翼和旋转体机身在大迎角下计入气流分离时的定常非线性气动载荷。采用两种方法:(1)定常流的松弛法;(2)陡然起动流的时间相依法。方法(1)对旋涡强度和自由涡的位置进行松弛迭代,取得了收敛的结果。方法(2)计算机翼陡然起动后一系列时刻的旋涡强度和自由涡的位置,直到结果趋近于常数解。亚音速流的压缩性效应是假设小扰动计算的。两种方法计算的结果很接近,和可以找到的实验数据也很接近。
In this paper, the steady non-linear aerodynamic loads of thin slats and rotating body with non-stick subsonic flow in any planar shape are calculated under high angle of attack. Two methods are used: (1) relaxation of steady flow; and (2) time dependent method of abrupt start-up flow. Method (1) Relaxation iteration of the vortex intensity and the position of free vortex, obtained the result of convergence. Method (2) calculates the vortex intensity and the position of free vortex at a series of moments after the wing has suddenly started up until the result approaches a constant solution. The compressibility effect of subsonic flow is assumed to be small perturbation calculations. The results of the two methods are very close, and the experimental data can be found very close.