节点文献
波纹壁面上的高超声速边界层气动降热（英文）
Reduced aerodynamic heating in a hypersonic boundary layer by a wavy wall
【摘要】 <正>Hypersonic boundary layer transition is of fundamental importance for the design of high-speed vehicles because of its direct relevance to drag and aerodynamic heating. As the focus of transition and turbulence research is shifting towards higher velocities,research on compressible flows, especially hypersonic flows, is becoming increasingly attractive to researchers worldwide [1,2].
【关键词】 边界层；
turbulence；
compressible；
aerodynamic；
attractive；
heating；
高超声速；
面上；
averaged；
波纹；
【基金】 supported by the National Natural Science Foundation of China (10921202, 11221061, 11632002, 11521091, 11602005, and 91752202);the National Key Project (GJXM92579)
- 【文献出处】 Science Bulletin ,科学通报(英文版) , 编辑部邮箱 ,2022年10期
- 【分类号】V231.1
- 【下载频次】37