摘要
在几何不可调的二元外压式斜极进气道的设计中，选择合理的斜板和唇口几何参数是最重要的问题之一。本文对一个设计马赫数为１．８的这类进气道的斜板和唇口参数进行了风洞、试验研究。用缩尺模型风洞试验，对比分析了不同斜板角和不同外侧唇口内唇角、唇缘半径对进气道内流特性的影响。结果表明，对确定的进气道布局，斜板角小的变化对进气道超音速内流总医恢复系数、稳态出口流场周向畸变指数及喘振裕度的影响很大，唇口参数小的改变却对亚音速内流特性并无所期待的明显影响，而对超音速的影响仍是大的。
A 1/11-scale model of a two-dimensional external compression supersonic inlet with maximum Mach number 1. 8 was tested from Mach 0. 8 to 1. 8. Theramp of the inlet is side-mounted vertically, its duct is bifurcated. The effects oframp angles, internal lip angles and circle lip radius on internal performances of theinlet are presented. The experimental results show that a small change of ramp angle causes large changes of inlet pressure recovery, circumferential steady-pressuredistortion and buzz margin, and small changes of internal lip angle and lip radius effect the changes in performances of inlet unobviously at subsonic, but apparently atsupersonic.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1994年第2期12-16,57,共6页
Journal of Propulsion Technology
关键词
风洞试验
进气道
进气道气流
Wind tunnel test,External compression inlet,Design parameter,Inlet flow,Experimental aerodynamics
