包含支撑装置和机翼变形的CRM-WB构型气动特性数值模拟  

Numerical simulation of aerodynamic characteristics of CRM-WB configuration with support system and wing deformation

作　　者：王运涛[1] 孙岩[2] 孟德虹[1] 张书俊[1] 杨小川[1] WANG Yuntao SUN Yan MENG Dehong ZHANG Shujun YANG Xiaochuan(Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 62 I000, China State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China)

机构地区：[1]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000 [2]中国空气动力研究与发展中心空气动力学国家重点实验室,绵阳621000

出　　处：《航空学报》2017年第10期45-53,共9页Acta Aeronautica et Astronautica Sinica

基　　金：国家重点研究发展计划(2016YFB0200700)~~

摘　　要：CRM(Common Research Model)是第四届~第六届AIAA阻力预测研讨会(DPW)选择的参考外形。第四届和第五届DPW会议气动特性数值模拟结果的统计分析表明试验与计算之间存在明显差异。采用CFD方法和流固耦合(FSC)方法数值模拟了带支撑装置的CRM翼身组合体(CRM-WBS)构型的气动特性,以评估模型支撑装置和静气动弹性变形对CRM翼身组合体(CRM-WB)构型气动特性数值模拟结果的影响。通过与不包含支撑装置的CRM-WB构型的数值模拟结果和NASA Langley NTF风洞试验结果的对比分析,CRM-WBS构型的CFD计算结果表明,支撑装置导致机翼上翼面激波位置前移,升力系数、阻力系数、低头力矩系数下降。CRM-WBS构型的流固耦合计算结果表明,静气动弹性变形主要影响机翼上表面激波位置并显著降低外侧机翼激波位置前的负压值,进一步导致升力系数、阻力系数、低头力矩系数下降。包含支撑装置和静气动弹性变形的CRM-WB构型气动特性数值模拟结果更加接近试验结果。Common Research Model （CRM） is the reference configuration selected by 4th-6th AIAA Drag Prediction Work- shop （DPW）. Statistical analyses of the numerical simulation results of aerodynamic characteristics from DPW IV and DPW V illustrate obvious difference between experimental and numerical data. To assess the influence of the support system and static aeroelastic deformation on the numerical simulation results of aerodynamic characteristics of CRM Wing-Body （CRM- WB） configuration,aerodynamic characteristics of CRM Wing-Body configuration with the Support system （CRM-WBS） are simulated with CFD method and Fluid-Structure Coupling （FSC） method. Compared with the CFD results of the CRM-WBS configuration without support system and the experimental data from the NASA Langley National Transonic Facility （NTF） wind tunnel,the CFD results of CRM-WBS configuration show that the support system can move the shock wave upward on the wing upper surface and decrease the lift coefficient,drag coefficient,and the nose-down pitching moment coefficient, The FSC numerical results of CRM-WBS configuration show that the static aeroelastic deformation mainly affects the shock wave position on the wing upper surface,decreases the negative pressure coefficient obviously before the shock wave on the out- ward part of the wing, and further decreases the lift coefficient, drag coefficient and nose-down pitching moment coefficient. Numerical simulation results of aerodynamic characteristics of CRM-WBS configuration and static aeroelastic deformation agree more with the experimental results.

关 键 词：CRM-WB构型 支撑装置 静气动弹性变形 气动特性 CFD 流固耦合 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]