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利用有限体积法离散求解雷诺平均Navier-Stokes方程,计算了具有不同机翼上反角的翼身组合体构型;着重研究了机翼上反角对纵向升阻、俯仰力矩特性的影响规律;并通过展向压力分布的对比,首次从机理上对这种影响进行了探索解释,为气动布局机翼安装参数的设计提供了思路和参考。研究结果表明:由于上反角主要改变了弦向前50%部分的压力分布,所以机翼上反角越大,前缘上表面吸力峰与下表面正压力下降越多,激波向前移动越大、强度更弱,从而升力、阻力、升阻比均减小。本文在上反角小于9°范围内,上反角每增加1°,升力系数降低0.005,阻力系数降低0.0002,升阻比降低0.04,俯仰力矩导数降低0.001,典型剖面压力最小值降低1%,激波位置前移1.6%。
The finite volume method is used to solve the Reynolds-averaged Navier-Stokes equations discretely. The configuration of the wing body with different wing anti-angles is calculated. The influence law of the wing anti-corner on the vertical lift and pitch moment characteristics is emphatically studied. Through the contrast of the pressure distribution in the exhibition direction, this kind of influence is explored and explained for the first time from mechanics, which provides the ideas and references for the design of the aerodynamic layout wing installation parameters. The results show that as the upper anti-angle mainly changes the pressure distribution in the first 50% of the chord, the larger the anti-angle on the wing, the more the pressure drop at the upper front surface and the lower surface are decreased, and the shock wave moves forward The larger, weaker, so lift, drag, lift resistance ratio are reduced. In this paper, when the upper dihedral angle is less than 9 °, the lift coefficient decreases by 0.005, the drag coefficient decreases by 0.0002, the drag ratio decreases by 0.04, the pitch moment derivative decreases by 0.001, the typical section pressure decreases by 1% Shock position moved forward by 1.6%.