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本文利用微扰动理论的波阻力积分公式, 推导了超音速旋转体与机翼当升力不为零时的波阻力公式, 应用这些公式得到细长旋转体与小展弦比机翼在一定的条件下的最小波阻力和对应的横截面积与升力顺气流方向的分布与外形,以及任意平面形状机翼的最小波阻力和对应的截面积与升力分布所满足的条件。最后, 建立了一个最佳超音速小展弦比机翼的极图公式, 并求解了最大升阻比问题。
In this paper, the wave resistance integral formula of the perturbation theory is used to derive the wave resistance formula of the supersonic rotor and the wing when the lift is not zero. The formulas of the drag resistance of the slender revolving body and the small aspect ratio wing are obtained under certain conditions Under the minimum wave resistance and the corresponding cross-sectional area and the direction of the lift along the flow direction and shape, as well as any plane shape wing minimum wave resistance and the corresponding cross-sectional area and lift distribution conditions. Finally, a pole figure formula of the optimal supersonic small aspect ratio airfoil is established, and the maximum lift-drag ratio problem is solved.