Control of severe shock-wave/boundary-layer interactions in hypersonic inlets
Document Type
Article
Publication Date
1-1-2018
Abstract
A theoretical analysis and numerical simulations are conducted to demonstrate the control capability of a splitter on the shock-wave/boundary-layer interactions in a generic hypersonic inlet with both a two-staged external compression and a strong cowl compression. The results show that, under the unstart condition, a well-designed splitter could suppress the massive cowl shock-induced separation, increase the fullness of the rampside boundary-layer profile at the isolator exit, and improve the inlet performance over the targeted operating Mach number range. With the splitter design, the severe shock-wave/boundary-layer interaction induced by the strong cowl shock is replaced by several weaker shock-wave/boundary-layer interactions with reduced shock intensity and boundary-layer thickness.
Publication Source (Journal or Book title)
Journal of Propulsion and Power
First Page
614
Last Page
623
Recommended Citation
Xie, W., Wu, Z., Yu, A., & Guo, S. (2018). Control of severe shock-wave/boundary-layer interactions in hypersonic inlets. Journal of Propulsion and Power, 34 (3), 614-623. https://doi.org/10.2514/1.B36614
