跨音速风洞翼型试验与数值仿真应用  

Application of airfoil test and numerical simulation in transonic wind tunnel

作　　者：马震宇 王正鹤 赵希玮 程兰兰 MA Zhenyu;WANG Zhenghe;ZHAO Xiwei;CHENG Lanlan(School of Aeronautical Engineering,Zhengzhou University of Aeronautics,Zhengzhou 450046,China;Aeronautical Engineering Graduate Team,Air Force Engineering University,Xi'an 710038,China;School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]郑州航空工业管理学院航空工程学院,河南郑州450046 [2]空军工程大学航空工程研究生队,陕西西安710038 [3]西北工业大学动力与能源学院,陕西西安710072

出　　处：《实验技术与管理》2020年第5期128-131,136,共5页Experimental Technology and Management

基　　金：河南省科技攻关计划项目(192102310471);郑州航空工业管理学院教研基金项目(zhjy18-11)

摘　　要：以FL-1风洞NACA0012翼型模型试验为研究对象,对实际三维黏性流场进行数值仿真,进口来流马赫数分别为0.5和0.8,模型攻角为3.05°。模型中部翼型表面绕流压强系数分布计算值与试验值符合良好,清晰呈现翼型表面附面层网格分布、可压缩流场流速和密度分布、局部激波及其诱导附面层分离。试验段上下透气孔板壁面模拟边界条件可行,迭代计算过程对来流马赫数实时监视和调控,能够确保其达到预定目标值。实际物理试验与计算机数值仿真相互配合、互相促进,能够有效提升教学质量。Taking the NACA0012 airfoil model test in the FL-1 wind tunnel as the research object,the actual 3D viscous flow field of the model test is simulated numerically.The Mach number of inlet inflow is 0.5 and 0.8 respectively,and the model angle of attack is 3.05°.The calculated pressure coefficient distribution of the airfoil surface in the central part of model is in good agreement with the experimental data,showing clearly the grid distribution of the airfoil surface boundary layer,the velocity and density distribution of the compressible flow field and the local shock wave and its induced boundary layer separation.The simulation boundary condition on the upper and lower porous plates of the test section is feasible.Real-time monitoring and control of the inflow Mach number during the iterative calculation process can ensure that the inflow Mach number reaches the target value.Practical physical experiment and computer numerical simulation can cooperate with each other,which can effectively improve the quality of teaching.

关 键 词：风洞试验 亚跨音速 翼型模型 数值仿真 来流马赫数监控 流场可视化 

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] V211.3