A Study on High Subsonic Airfoil Flows in Relatively High Reynolds Number by Using OpenFOAM  

作　　者：Shinichiro NAKAO Masashi KASHITANI Takeshi Miyaguni Yutaka YAMAGUCHI 

机构地区：[1]Department of Mechanical Engineering,Nagasaki Institute of Applied Science,536 Aba-Machi,Nagasaki,851-0193,JAPAN [2]Department of Aerospace Engineering,National Defense Academy,1-10-20 Hashirimizu,Yokosuka,239-8686,JAPAN

出　　处：《Journal of Thermal Science》2014年第2期133-137,共5页热科学学报（英文版）

摘　　要：In the present study,numerical calculations of the flow-field around the airfoil model are performed by using the OpenFOAM in high subsonic flows.The airfoil model is NACA 64A010.The maximum thickness is 10 % of the chord length.The SonicFOAM and the RhoCentralFOAM are selected as the solver in high subsonic flows.The grid point is 158,000 and the Mach numbers are 0.277 and 0.569 respectively.The CFD data are compared with the experimental data performed by the cryogenic wind tunnel in the past.The results are as follows.The numerical results of the pressure coefficient distribution on the model surface calculated by the SonicFOAM solver showed good agreement with the experimental data measured by the cryogenic wind tunnel.And the data calculated by the SonicFOAM have the capability for the quantitative comparison of the experimental data at low angle of attack.

关 键 词：OPENFOAM High Subsonic Flows Cryogenic Wind Tunnel AIRFOIL 

分 类 号：O35[理学—流体力学]