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应用后缘主动变弯度技术的机翼能够改善飞行器的气动性能,其气动特性的研究对于未来可变形机翼的设计具有重要意义。以柔性后缘可连续变弯度二元机翼为研究对象,在Fluent计算平台上采用可压缩Navier-Stokes方程和Spalart-Allmaras(S-A)湍流模型进行气动力数值研究,从压力分布、流场结构和机翼变形方式等方面分析了可变形机翼的气动特性。数值计算结果表明,可变形机翼升力线斜率和最大升力系数与常规带简单襟翼的机翼基本一致,但失速攻角较小;在失速之前,可变形机翼具有较高的升力系数和升阻比,但同时产生较大的低头力矩。柔性后缘下偏到一定角度可以抑制后缘涡的前传,在失速后升力系数出现缓慢上升,增大了有效攻角的范围,具有较好的失速特性。
The wing with the active camber technology of trailing edge can improve the aerodynamic performance of the aircraft. The study of its aerodynamic characteristics is of great significance to the future deformable wing design. In this paper, the aerodynamic numerical study of a flexible trailing-edge continuous variable-curvature binary wing is carried out on a Fluent computational platform using the compressible Navier-Stokes equations and the Spalart-Allmaras (SA) turbulence model. From the pressure distribution, the flow field structure And wing deformation methods and other aspects of the aerodynamic characteristics of deformable wings. The numerical results show that the slope of the lift line and the maximum lift coefficient of the deformable wing are basically the same as the conventional wings with simple flaps, but the angle of attack is small. Before delaying, the deformable wing has a higher lift coefficient and Ascension ratio, but at the same time produce a larger bow torque. When the flexible trailing edge is deviated by a certain angle, the trailing edge eddy can be suppressed. After the stall, the lift coefficient increases slowly, which increases the range of effective angle of attack and has better stalling characteristics.