Affiliation of Author(s):能源与动力学院

Journal:Hangkong Dongli Xuebao

Abstract:To aid in understanding the flow mechanism in supersonic inlet under the over-speed state, a numerical simulation was performed to obtain the flow structure of a rectangular inlet whose design Mach number was 2.0, operating under different inflow Mach numbers and backpressures. Results indicate: for the design case of Mach number 2.0, the core flow of shock train was deflected from the cowl-side surface to the ramp-side surface associated with the backpressure increase. While the inlet operated under the over-speed state, the core flow of shock train was deflected to the ramp-side surface firstly and then to the cowl-side surface due to the effects of the cowl-lip separation bubbles and the cowl shock in turn. For the case of inflow Mach number 2.5, a Mach-stem appeared at the joint point between forebody oblique shock and cowl shock once the backpressure increaseed to a certain value. However, this flow structure didn't appear in the case of inflow Mach number 3.0. Under the above two over-speed states, with the increase of backpressures, the transmit shock of forebody oblique shock was transformed into normal shock, and the transmit shock of cowl shock also changed its shape. © 2017, Editorial Department of Journal of Aerospace Power. All right reserved.

ISSN No.:1000-8055

Translation or Not:no

Date of Publication:2017-05-01

Co-author:饶彩燕

Correspondence Author:Tan Huijun