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 

作者机构：Department of Mechanical EngineeringNagasaki Institute of Applied Science536 Aba-MachiNagasaki851-0193JAPAN Department of Aerospace EngineeringNational Defense Academy1-10-20 HashirimizuYokosuka239-8686JAPAN 

出 版 物：《Journal of Thermal Science》 (热科学学报（英文版）)

年 卷 期：2014年第23卷第2期

页      面：133-137页

核心收录：

学科分类：080704[工学-流体机械及工程] 080103[工学-流体力学] 08[工学] 0807[工学-动力工程及工程热物理] 0801[工学-力学（可授工学、理学学位）] 

主　　题：OpenFOAM High Subsonic Flows Cryogenic Wind Tunnel Airfoil 

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 *** airfoil model is NACA *** maximum thickness is 10 % of the chord *** SonicFOAM and the RhoCentralFOAM are selected as the solver in high subsonic *** grid point is 158,000 and the Mach numbers are 0.277 and 0.569 *** CFD data are compared with the experimental data performed by the cryogenic wind tunnel in the *** results are as *** 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 *** the data calculated by the SonicFOAM have the capability for the quantitative comparison of the experimental data at low angle of attack.