摘要
采用在边界层中引入控制装置的方法进行湍流减阻问题研究 .着重研究了对于正确模拟减阻过程至关重要的湍流模型 ,不同的模型 (包括Johnson King涡粘 /雷诺应力封闭模型和对近壁区的低雷诺数流动作修正的k ε模型 )用于NS方程的数值模拟 .计算从控制装置的上游开始 ,其结果更为准确可靠 .为得到最佳减阻效果 ,分析研究了装置的排列和参数的影响 ,给出了单个装置和并排双装置的典型减阻结果 。
Turbulent flow drag reduction by in-flow manipulator devices with various parameters in boundary layer is studied computationally in this paper. Different turbulent models, which is very important for studying the process of reduction drag of the turbulent flow, including Johnson-King eddy-viscosity/Reynolds-stress closure model and k-ε model with the improvement for low Reynolds number flow at near wall, are used in the computation of Navier-Stokes equation. equation. The calculation starts from up stream of the manipulator devices, and results obtained will be more accurate. The effect of different parameters of manipulator devices including single and double devices are studied, and used in optimization of drag reduction. The results obtained are compared well with date of the experiments.
出处
《弹道学报》
EI
CSCD
北大核心
2001年第4期28-33,共6页
Journal of Ballistics
基金
航空科学基金资助项目 (98A5 2 0 0 8)
关键词
减阻
湍流边界层
大涡破碎装置
湍流模型
飞行器
drag reduotion, turbulent boundary layer, large eddy break up (LEBU), turbulent model