基于后缘襟翼偏转的大型客机变弯度技术减阻收益  

Drag reduction benefits of variable camber technology of airliner based on trailing-edge flap deflection

作　　者：何萌 杨体浩 白俊强[2] 杨一雄 HE Meng;YANG Tihao;BAI Junqiang;YANG Yixiong(School of Aeronautics,Northwestern Polytechnical University,Xi'an 710072,China;Unmanned System Research Institute,Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]西北工业大学无人系统技术研究院,西安710072

出　　处：《航空学报》2020年第7期159-174,共16页Acta Aeronautica et Astronautica Sinica

摘　　要：为了满足工程实际约束,针对宽体客机内外襟翼位置与偏角卡位进行了机翼后缘变弯度减阻收益研究。使用雷诺-平均Navier-Stokes(RANS)方程对襟翼不同后缘偏角采用遍历的方式进行了气动力评估,得到后缘襟翼最佳偏角;探究了变弯度技术在非设计点的减阻收益,以及变弯度技术对宽体客机阻力发散和抖振边界设计要求的拓展能力,进一步采用远场阻力分解方法探究了设计结果的减阻机理。结果表明,在变马赫数的非设计点,考虑俯仰力矩系数配平之前,阻力能获得一些收益,但考虑俯仰力矩系数配平后,变弯度后的阻力系数不减反增;当升力系数发生变化时,变弯度在考虑俯仰力矩配平的情况下,均能取得一定的收益;变弯度技术也减缓了抖振点激波诱导分离的趋势,对抖振特性有较好的改善作用。基于后缘襟翼偏转的变弯度减阻收益评估和机理分析,能为宽体客机机翼变弯度设计提供参考。To satisfy the practical constraints of engineering projects,this study examines the drag reduction caused by morphing trailing-edge wings based on the position of the inner and outer flaps of the wide-body aircraft and the deflection position.Aerodynamic evaluations based on the Reynolds-Averaged Navier-Stokes(RANS)equation are conducted on all the deflection angles of the flaps,obtaining the optimal deflection angle of the trailing edge flaps.Benefits of the variable camber technology are investigated,including the expansion of the design requirements for the buffet and drag-divergence boundary as well as the drag reduction at other non-design points.Furthermore,the far field drag decomposition method is used to explore the drag reduction mechanism of the design results.Results show that at the non-design points of the variable Mach number,the drag reduction can be obtained regardless of the trimming moment.However,the drag is not decreased while considering the trimming moment.With different cruise lift coefficients,the variable camber technology can invariably achieve certain drag reduction when considering the trimming moment.Moreover,the variable camber technology can also slow the trend of shock-induced separation and improve the buffeting characteristics of the wing.The drag reduction evaluation and mechanism analysis of the variable camber technology based on trailing edge flap deflection provide reference for the variable camber design of wide-body airliner wings.

关 键 词：大型客机设计 后缘变弯度 力矩配平 阻力发散 抖振 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]