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利用有限体积法离散可压缩Euler方程,计算了带5种不同类型翼梢小翼的全机高速巡航外形。重点研究了不同小翼对飞机横航向静稳定性、机翼压力中心移动量和侧滑时滚转力矩系数随迎角变化的影响规律。研究结果表明:(1)翼梢小翼均不降低飞机的横向静稳定性,都将降低飞机的航向稳定性;(2)翼梢小翼均使机翼压力中心向外移动,小后掠角的传统小翼移动量最大,鲨鱼鳍型小翼的移动量最小;(3)小翼均没有改变全机滚转力矩系数随迎角的非线性变化趋势;(4)侧滑时滚转力矩系数随迎角的非线性变化主要是由于左右两翼作用力的差量引起的。
Using the finite volume method to discretize the compressible Euler equation, the cruise contour of the whole machine with five different types of wingtips has been calculated. Focus on the different winglets on the aircraft’s lateral stability, the center of the airfoil movement and rolling moment coefficient when the angle of attack changes with the impact of law. The results show that: (1) Winglets do not reduce the lateral static stability of the aircraft, both of them will reduce the stability of the aircraft; (2) Winglets move the center of wing pressure outward, (3) Winglets did not change the whole machine rolling torque coefficient with the angle of attack non-linear trend; (4) roll when the side slip The nonlinear variation of torque coefficient with the angle of attack is mainly caused by the difference of the left and right wing forces.