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后缘连续变弯度机翼在提高民用客机气动特性方面有较大的潜力,近年来被广泛关注。基于建立的全局优化设计系统,研究了机翼后缘连续变弯度对宽体客机翼身组合体气动特性的影响。首先,采用自由型面变形(FFD)技术建立了后缘连续变弯度的参数化方法。然后,采用RANS方程作为流场评估方法,针对翼身组合体构型设计点附近升力系数开展了机翼后缘连续变弯度气动减阻优化设计。最后,探索了仅外翼段后缘连续变弯度和内外翼后缘均连续变弯度优化设计结果的异同。优化结果表明,升力系数小于设计升力系数时,在只考虑外翼段后缘连续变弯度的设计中,不易实现激波阻力和诱导阻力同时降低,考虑内翼段后缘连续变弯度后,减阻量较前者更为明显;升力系数大于设计升力系数时,外翼段和内外翼的后缘偏转均可实现诱导阻力和激波阻力的同时降低,且减阻量相差不大。
The trailing edge continuous turning camber wing has great potential in improving the aerodynamic characteristics of civil aircraft, and has been widely concerned in recent years. Based on the established global optimization design system, the effect of continuous turning on the trailing edge of the wing on the aerodynamic characteristics of a wide body passenger aircraft wing assembly is studied. First of all, a parametric method of continuous camber of trailing edge was established by using free surface deformation (FFD) technique. Then, using the RANS equation as the flow field assessment method, aiming at the lift coefficient near the design point of the wing-body assembly, the aerodynamic drag reducing optimization of the trailing edge of the wing was carried out. Finally, the similarities and differences between the results of continuous curvature optimization of only the outer edge of the outer segment and the continuous variation of the trailing edge of the inner and outer wings were explored. The optimization results show that when the lift coefficient is less than the design lift coefficient, it is not easy to reduce both the shock resistance and the induced resistance in the design considering only the continuous camber of the trailing edge of the outer wing segment. After considering the continuous camber of the trailing edge of the inner wing segment, The resistance is more obvious than the former; when the lift coefficient is greater than the design lift coefficient, the trailing edge deflection of the outer wing segments and the inner and outer wings can both reduce the induced resistance and the shock resistance, and the drag reduction amounts are not much different.