自适应与双目标优化机翼的气动特性比较

在二维翼型自适应的研究基础上,用Powell法优化计算了对前缘后掠角为35°,展弦比为3.9,梢根比为0.17,机翼剖面为NACA65006翼型的梯形翼的前后缘舵面偏转角,从而获得了在亚跨声速时升阻比大而在超声速时阻力系数小的自适应机翼的最优气动外形.采用了并行遗传算法,计算了要求亚跨声速升阻比大同时超声速阻力小的气动双目标优化机翼的外形.讨论了优化机翼相对于原始机翼的气动增益.与二维一样,三维数值算例也证明了自适应机翼可获得明显的气动增益. 

Comparison between adaptive and biobjective optimization wing's aerodynamic features

Based on two dimensional airfoil adaptation, the deflected angles of leading edge and training edge of a three dimensions wing having 35° leading edge sweep angle, aspect ratio of 3.9, taper ratio of 0.17 and taking NACA65006 as wing section were calculated by using powell method to obtain an adaptive wing configuration having high lift/drag at subsonic/transsonic flight and low drag at supersonic flight. A biobjective optimizal wing was also designed for above 2 objectives, by using parallel Genetic Algorithm. The relative aerodynamical gains of both two optimal wings over the original wing were analyzed. Numerical results show that the adaptive wing can also obtain higher gains over the original and biobjective wings ,as illustrated in two dimensions.