高超音速可渗透表面边界层的流动和传热分析  

Flow and Heat Transfer Analysis of Hypersonic Permeable Surface Boundary Layer

作　　者：马源 张艳 

机构地区：[1]北京建筑大学理学院,北京

出　　处：《应用数学进展》2024年第12期5129-5135,共7页Advances in Applied Mathematics

基　　金：国家自然科学基金(Nos. 22478028, 22178022)。

摘　　要：本文研究了具有气体注入的高超音速边界层流动和传热规律。考虑了气体注入强度对边界层流动和传热的影响,建立了具有气体注入的高超音速边界层流动和传热控制方程。通过合适的相似变换将偏微分控制方程转化为常微分方程组,同时利用同伦分析法获得了常微分方程组的解。绘图讨论了注入参数对速度场和温度场的影响。This paper investigates the flow and heat transfer laws of hypersonic boundary layer with gas injection. Considering the influence of gas injection intensity on boundary layer flow and heat transfer, a control equation for hypersonic boundary layer flow and heat transfer with gas injection was established. By using appropriate similarity transformations, the partial differential control equations were transformed into a system of ordinary differential equations, and the solution of the system of ordinary differential equations was obtained using homotopy analysis. The graph discusses the influence of injection parameters on velocity and temperature fields.

关 键 词：高超音速边界层 可渗透表面 气体注入 同伦分析法 

分 类 号：O17[理学—数学]