大型客机远场阻力分解方法验证研究  

Civil Aviation Aircraft Drag Prediction using Far-field Drag Decomposition Method

作　　者：李典 郝海兵[1] 颜洪[1] 梁益华[1] LI Dian;HAO Hai bing;YAN Hong;LIANG Yi hua(Xi′an Aeronautics Computing Technique Research Institute,AVIC,Xi′an 710068,China)

机构地区：[1]航空工业西安航空计算技术研究所,陕西西安710068

出　　处：《航空计算技术》2018年第5期5-10,共6页Aeronautical Computing Technique

基　　金：国家973计划项目资助(50976017);国家863计划项目资助(2012AA01A304)

摘　　要：基于动量定理推导了远场阻力分解方法,发展了一套高精度流场阻力辨识和分解后置处理工具Mfd3。通过对计算流场区域有效辨识,采用域积分方式获取阻力各组分的精确估计,包括激波阻力、粘性阻力、诱导阻力和数值耗散阻力,从而克服传统近场阻力积分方法无法消除CFD数值耗散的影响以及无法反映阻力产生的物理机制等缺点。翼身组合体标模计算结果表明:远场阻力分解方法能够清楚地给出由粘性和激波产生的熵增分布,并能识别出各自的贡献区域;同近场阻力积分方法相比,远场阻力积分方法不仅可以消除数值耗散阻力从而提高阻力的计算精度,而且还能获取阻力构成分量,便于分析阻力产生的机理,并能进一步用于工业部门获取减阻的细致物理机制。Based on the far field drag decomposition method derived from momentum theorem,a set of post processing tool for high precision drag identification is developed.All components of drag including wave drag,wake drag,induced drag and numerical dissipative drag are predicted through the effective identification and integration of corresponding regions.The numerical results of wing body model and a civil airliner show that the far field drag decomposition method obtains clearly the entropy increasedistribution caused by viscous dissipation and shock waves and identifiesreasonablyall influence regions.Compared with the near field drag integral method,the far field drag decomposition method is capable of eliminating the influence of numerical dissipation and exporting the physical mechanism of drag,which can be further used to get the detailed physical mechanism of drag reduction.

关 键 词：民机 近场阻力 远场阻力 诱导阻力 粘性阻力 激波阻力 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]