外压式二元与轴对称进气道设计及性能对比  

Design and Performance Comparative for the 2-D and Axisymmetric External-compression Inlet

作　　者：胡声超[1] 鲍福廷[1] 赵瑜[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《科学技术与工程》2011年第31期7746-7749,共4页Science Technology and Engineering

摘　　要：给出了二元和轴对称两种不同结构形式的进气道进行理论最优设计方法;并以飞行马赫数Ma=2.5,高度H=10km为设计点,计算和比较了两种进气道的性能。结果表明在相同情况下,二元进气道具有相对较高的总压恢复系数,但轴对称进气道出口的气流较均匀、畸变较小,并且马赫数较低。这一结果可为冲压发动机进气道结构形式的选择提供理论依据。Academic optimal design method of the 2-D and axisymmetric external-compression supersonic inlet were presented. After design, the performance of two different types inlet are calculated and compared in the design point Ma =- 2.5, H = 10 km. The results show that, in the same condition, 2-D inlet have higher total pressure recovery coefficient but the outlet flow of axisymmetric inlet ＇is uniform and has a smaller distortion coefficient, a lower Mach number. The result could provide references for the choice of the type of supersonic inlet.

关 键 词：进气道 二元 轴对称 设计 性能对比 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]