Affiliation of Author(s):能源与动力学院

Journal:Tuijin Jishu

Abstract:To reveal the particular flow mechanism of low-boom inlet, a rectangular low-boom supersonic inlet is designed, which features a zero-angle cowl and relaxed isentropic compression forebody. A numerical simulation was performed to obtain the flow structure and operating characteristics of the rectangular low-boom inlet working at different operating conditions. The results show that due to the large deflection angle of cowl internal surface, a curve shock and a corresponding subsonic region are formed near the entrance of the low-boom inlet, and the existence of these flow structure reduce the total pressure recovery by 2.3% and 5.5% compared with the external compression inlet in lower incoming Mach number of 1.8 and 2.0 under critical state. While the incoming Mach number becomes higher([Ma∞=2.5), a large separation bubble induced by the cowl oblique shock appears in the downstream of the shoulder. The inlet performance is sensitive to the blockage with the influence of this separation bubble. In addition, the boom of the low-boom inlet is decreased significantly because of zero-angle cowl. And the boom of low-boom inlet is reduced by 98.6% compared with the regular supersonic inlet when the inlet operates under fully opened state for the case of Mach 2.0. Moreover, the sonic boom of the supersonic inlet is associated with its operating state with the larger degree of shock spillage and the lower coming flow, Mach number will increase the sonic boom. © 2017, Editorial Department of Journal of Propulsion Technology. All right reserved.

ISSN No.:1001-4055

Translation or Not:no

Date of Publication:2017-05-01

Co-author:饶彩燕,F70206449

Correspondence Author:Tan Huijun