火箭推进2017，Vol.43Issue(6)：54-60,7.
二维超声速进气道扩张段性能计算
Performance calculation of two-dimensional supersonic inlet diffuser
汪昆 1谢旅荣 2刘雨1
作者信息
- 1. 南京航空航天大学 能源与动力学院, 江苏 南京210016
- 2. 江苏省航空动力系统重点实验室, 江苏 南京210016
- 折叠
摘要
Abstract
The influences of the law of centerline variation, expansion ratio and centerline offset of two-dimensional supersonic inlet diffuser on aerodynamic performance and flow characteristics under inlet design condition are studied. The numerical results indicate that the inlet with diffuser rapid turning at its exit has maximum total pressure recovery coefficient and inlet with diffuser rapid turning at the entrance has minimum total pressure recovery coefficient; as the expansion ratio increases from 1. 40 to 1. 80, inlet total pressure recovery coefficient and backpressure-resistance ability decrease, and the exit Mach number increase; the effect of expansion ratio and length on inlet exit parameter has a strong coupling relationship. As offset ratio increases, the inlet total pressure recovery coeffi-cient increases at the beginning, but as the offset ratio increases to more than 0. 80, the inlet total pressure recovery coefficient declines and the exit Mach number increases. General speaking, the var-iation of offset ratio has little effect on backpressure-resistance ability of the inlet.关键词
超声速进气道/进气道扩张段/中心线变化规律/扩张比/中心线偏距Key words
supersonic inlet/inlet diffuser/law of centerline variation/expansion ratio/cen-terline offset分类
航空航天引用本文复制引用
汪昆,谢旅荣,刘雨..二维超声速进气道扩张段性能计算[J].火箭推进,2017,43(6):54-60,7.
