二元混压超音速进气道湍流流场数值模拟  

Numerical Simulation of Turbulent Flow in 2-D Mixed-Compression Supersonic Inlet

作　　者：李进贤[1] 王国辉[1] 高朝辉 蔡体敏[1] 郭颜红[2] 蔡选义 

机构地区：[1]西北工业大学航天工程学院,西安710072 [2]中国航空工业总公司第014中心,洛阳471009

出　　处：《固体火箭技术》2000年第2期16-20,共5页Journal of Solid Rocket Technology

摘　　要：对二元混压超音速进气道湍流流场进行了数值模拟。计算中将无波动无自由参数耗散差分格式与对流迎风矢通量分裂技术耦合使用 ,应用 Baldwin-L om ax代数湍流模型 ,按照 Mac Cormack时间分裂方法对贴体坐标系下二维雷诺平均 N-S方程进行差分离散 ,模拟了二元混压超音速进气道在临界和非临界流动状态下整个流场的流动情况。The turbulent flow in 2 D mixed compression supersonic inlet is simulated by numerical method.During the calculations,non oscillatory containing no free parameters and dissipative (NND) format and advection upstream splitting method (AUSM) are combined,and the Baldwin Lomax turbulent model and MacCormack time splitting method are applied to discrete the Reynold average Navier Stokes equation in two dimensinoal generalized coordinates with finite difference.Applying this algorithm,critical and non critical flow status of whole flow field are simulated in 2 D mixed compression supersonic inlet.The calculated results of inlet main portion are in accord with theoretical analysis.

关 键 词：冲压喷气发动机 超音速进气道 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程] V235.21