空气动力学学报2011，Vol.29Issue(1)：68-72,5.
高超声速进气道壁面开缝对边界层分离影响研究
Study on the effect of wall slotting on boundary layer separation in hypersonic inlet
摘要
Abstract
Taking 2-D hypersonic inlet GK01 as the computational model, inviscid and viscous calculations, as well as boundary layer separation control method on the inlet were numerically studied. The results showed that, the measure of slotting designed in the paper can effectively reduce or even eliminate the boundary layer separation phenomenon induced by shock / boundary layer interaction and decrease the negative effects of viscous effects. Before adopting measure relatively, the slotting can significantly improve the inlet total pressure recovery coefficient and kinetic energy efficiency at design and off-design point, while has little effect on mass capture coefficient. Meanwhile, the effect of slotting on the inlet's performance index at the off-design point is given in this paper.关键词
高超声速进气道/边界层分离/开缝/总压恢复系数Key words
hypersonic inlet/ boundary layer separation/ slotted/ total pressure recovery coefficient分类
航空航天引用本文复制引用
李世珍,唐硕..高超声速进气道壁面开缝对边界层分离影响研究[J].空气动力学学报,2011,29(1):68-72,5.基金项目
国防基础科研项目,国家自然科学基金(10572115). （10572115）
