摘要
目前飞行器的气动设计主要以风洞实验和数值计算为主要手段。但是风洞实验的周期长、成本高。为提高设计性能,提出选取计算流体力学作为研究方法,并通过选用SST、k-ω和k-ε湍流模型对典型RAE2822翼型进行数值仿真,与风洞实验结果用图和表的形式进行比较,并分析仿真结果,对数值计算方法进行精度确认。结果表明所采用的计算流体力学在SST湍流模型的计算精度高,且满足计算要求,可以进一步为飞行器气动数值计算分析提供可靠的方法基础,进而为飞行器的设计工作打下了基础。
At present, the flight vehicle aerodynamic design takes wind tunnel test and numerical calculation as the main means. But wind tunnel experimental cycle is long, and the cost is high. This paper put forward the compu- tational fluid mechanics as the research method, and through the selection of SST, k - toand k - eturbulence model for numerical simulation with typical RAE2822 profile, and compared with wind tunnel experimental results using pic- tures and tables. The analysis of the simulation results was carried out and the accuracy of the numerical calculation method was confirmed. The results have shown that the use of computational fluid mechanics in the SST turbulence model is of high calculation precision, and it can meet the requirements and be further calculated for vehicle aerody- namic numerical calculation and analysis to provide reliable method for foundation.
出处
《计算机仿真》
CSCD
北大核心
2013年第4期116-119,141,共5页
Computer Simulation
关键词
飞行器
计算流体力学
翼型
湍流模型
： Flight vehicle
Computational fluid dynamics
Profile
Turbulence model
