|
|||||
|
|
| 高马赫数下激波湍流边界层干扰数值研究 | |
| 引用本文： | 闫文辉,吴小虹,徐晶磊,高歌.高马赫数下激波湍流边界层干扰数值研究[J].航空计算技术,2011,41(5):56-60. |
| 作者姓名： | 闫文辉 吴小虹 徐晶磊 高歌 |
| 作者单位： | 1. 中国航空研究院,北京,100012 2. 中航工业黎明航空发动机集团公司技术中心设计所,辽宁沈阳,110043 3. 北京航空航天大学航空发动机气动热力国防重点实验室,北京,100091 |
| 基金项目： | 北京航空航天大学“凡舟”青年科研基金项目资助(20110403) |
| 摘 要： | 应用GAO—YONG可压缩湍流方程组数值模拟了入射斜激波／平板湍流边界层相互干扰现象，计算了来流马赫数为5．0，激波入射角度分别为15．876°、23．287°两种不同激波干扰强度下的流场。计算程序中的对流项、扩散项分别采用二阶ROE格式和二阶中心差分格式离散，并用多步Runge—Kutta显式时间推进法求解空间离散后的控制方程。计算较好地模拟了高马赫数下的激波／湍流边界层干扰的流场结构，位移边界层厚度，动量损失厚度等，也比较准确地预测了平板壁面压力、摩阻系数等气动力参数的分布。 |
| 关 键 词： | 激波边界层干扰 湍流 计算流体力学 GAO—YONG可压缩湍流方程组 |
Numerical Study of Shock-wave Turbulent Boundary Layer Interaction at High Mach Number |
|
| YAN Wen-hui,WU Xiao-hong,XU Jing-lei,GAO Ge.Numerical Study of Shock-wave Turbulent Boundary Layer Interaction at High Mach Number[J].Aeronautical Computer Technique,2011,41(5):56-60. | |
| Authors: | YAN Wen-hui WU Xiao-hong XU Jing-lei GAO Ge |
| Institution: | YAN Wen-hui1,WU Xiao-hong2,XU Jing-lei3,GAO Ge3(1.Chinese Aeronautical Establishment,Beijing 100012,China,2.Design Institude of Eechno-center,Aviation Liming Aerospace Engine Group Inc,Shenyang 110043,3.School of Jet Propulsion,Beihang University,Beijing 100091,China) |
| Abstract: | Numerical simulations of oblique Shock-wave turbulent boundary-layer interaction on flat plate using GAO-YONG compressible turbulence equations are presented.This paper presents two cases with different incident shock angles,15.876°and 23.287°with the same free-stream Mach number 5.0 which induce attached and detached flows.Convection terms and diffusion terms are calculated using ROE scheme and CD(center difference) scheme respectively.The Runge-Kutta time marching method is employed to solve space discrete control equations.Typical flow features of Shock-wave turbulent boundary-layer interaction are described well in simulation.Meanwhile,calculations accurately predict distribution of pressure on flat plate,skin friction number and Stanton number.Good agreements between the calculations and experiment are obtained. |
| Keywords: | shock-wave turbulent boundary-layer interaction turbulent flow computational fluid dynamics GAO-YONG compressible turbulent equations |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ | |