进气道激波-边界层两种控制方法数值模拟研究

Translated title of the contribution: Numerical Simulation of Two Control Methods for Shock Waves-Boundary Layer Interactions in High-Speed Inlet

Youde Xiong, Renfu Li*, Ling Zhou

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

1 Citation (Scopus)

Abstract

In order to reduce the influence of shock waves and boundary layer interactions in high-speed inlet, a numerical simulation is conducted respectively on a 2D inlet with passive blowing and bleeding control and pressure relief control. Firstly, variations of field structure and field quality after applying two control methods at inlet throat, where the large-scale separation zone caused by shock waves-boundary layer interactions exists, are analyzed. It is found that both control methods can reduce the range of separation zone, can decrease the pressure and the speed of reflow in the separation zone, and can improve the uniformity of flow field. Then the performances of two control methods at different Mach numbers are compared. The results show that both control methods can significantly reduce the unstart Mach number and improve the total pressure recovery coefficient, and the pressure relief control has a better performance than the passive blowing and bleeding control, but the latter does not bring the influence of flow loss and static-pressure-ratio reduction.

Translated title of the contributionNumerical Simulation of Two Control Methods for Shock Waves-Boundary Layer Interactions in High-Speed Inlet
Original languageChinese (Traditional)
Pages (from-to)63-68
Number of pages6
JournalAero Weaponry
Volume26
Issue number5
DOIs
Publication statusPublished - 31 Oct 2019

Fingerprint

Dive into the research topics of 'Numerical Simulation of Two Control Methods for Shock Waves-Boundary Layer Interactions in High-Speed Inlet'. Together they form a unique fingerprint.

Cite this

Xiong, Y., Li, R., & Zhou, L. (2019). 进气道激波-边界层两种控制方法数值模拟研究. Aero Weaponry, 26(5), 63-68. https://doi.org/10.12132/ISSN.1673-5048.2018.0080