二元低音爆超声速进气道的流动特性研究

推进技术 ›› 2017, Vol. 38 ›› Issue (5): 975-982.

二元低音爆超声速进气道的流动特性研究

饶彩燕,谭慧俊,张悦

南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016

发布日期:2021-08-15
作者简介:饶彩燕，女，硕士生，研究领域为内流空气动力学。
基金资助:
江苏省普通高校研究生实践创新计划项目(SJLX15_0106)；中央高校基本科研业务费专项资金资助；

Flow Characteristics of a Rectangular Low-Boom Supersonic Inlet

Nanjing?University?of?Aeronautics?and?Astronautics，Jiangsu?Province?Key?Laboratory?of?Aerospace?Power?System， Nanjng 210016，China,Nanjing?University?of?Aeronautics?and?Astronautics，Jiangsu?Province?Key?Laboratory?of?Aerospace?Power?System， Nanjng 210016，China and Nanjing?University?of?Aeronautics?and?Astronautics，Jiangsu?Province?Key?Laboratory?of?Aerospace?Power?System， Nanjng 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 为了揭示低音爆进气道的特殊流动机理，设计了一种新型二元低音爆超声速进气道，其具有零度角唇罩和发散等熵压缩前体这两个典型特征，并通过仿真手段获得了其在典型状态下的流场结构和工作特性。结果表明:由于唇罩内侧倾角过大，在低来流马赫数下([Ma∞]=1.8，2.0)，低音爆进气道在口部产生了唇罩弯曲激波及相应的局部亚声速区，这一流动结构的存在使其在临界状态下的总压恢复系数与外压式进气道相比分别降低了2.3%和5.5%；而在高来流马赫数下([Ma∞]=2.5)，唇罩激波在肩部下游诱导出一个大的分离包，该分离包使得低音爆进气道的性能随下游堵塞度的变化变得敏感。由于本文设计的低音爆进气道外唇罩角为0°，其音爆水平与外压式进气道相比显著降低，其中其音爆在设计马赫数的通流状态下减小了98.6%。此外，进气道的音爆还与其工作状态相关，进气道的溢流程度越大、超声速来流的马赫数越低，音爆水平则越高。

关键词: 低音爆；超声速进气道；发散等熵压缩；零度角唇罩；弯曲激波；局部亚声速区

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.

Key words: Low-boom；Supersonic inlet；Relaxed isentropic compression；Zero-angle cowl；Curve shock；Partial subsonic region

饶彩燕,谭慧俊,张悦. 二元低音爆超声速进气道的流动特性研究[J]. 推进技术, 2017, 38(5): 975-982.

RAO Cai-yan,TAN Hui-jun,ZHANG Yue. Flow Characteristics of a Rectangular Low-Boom Supersonic Inlet[J]. Journal of Propulsion Technology, 2017, 38(5): 975-982.

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