跨声速机翼阻力分解的一种改进方法

An improved drag decomposition method for transonic wing

提出黏性区域探测器的一种改进形式,并用于捕捉激波和翼梢涡的熵增阻力;给出尾迹平面的可压缩涡动力学诱导阻力表达式,并与基于热力学的诱导阻力对比。在跨声速来流状态下,对ONERA M6和某民用飞机巡航状态下的机翼阻力进行分解,同时分析该民用飞机机翼安装翼梢小翼前、后的远场阻力构成。结果表明:新的区域探测器合理可靠,黏性阻力与伪熵阻力的计算结果更加准确;2种诱导阻力计算方式的计算结果一致,但基于涡动力学的诱导阻力计算方法受积分平面位置的影响更小;安装翼梢小翼基本不影响整个流场的黏性阻力,减阻的主要效果体现为诱导阻力的减小。

An improved viscous zone detector is proposed to capture the entropy drag of shock wave and wingtip vortex. The induced drag calculation based on compressible vortex force on the wake plane is derived. The induced drag is compared with the thermodynamical one. The wing drags of ONERA M6 and a civil aircraft in cruise state are decomposed under transonic incoming flow. The far-field drag composition of the civil aircraft is analyzed before and after the winglet installation. The results show that the new zone detector is reasonable and reliable, and the calculation results of viscous drag and spurious entropy drag are more accurate. Both of the two induced drag calculation methods can obtain consistent results, and the induced drag based on vortex force is less affected by the integral plane position. The installation of the winglet does not affect the viscous drag of the entire flow field, and the main effect of drag reduction is the reduction of induced drag.