摘要
通过对一种Caret型进气道进行试验与流场数值计算研究 ,给出该型进气道亚音速的基本气动特性 .在低速情况下 ,进 发匹配点处由于流量系数较大 ,管道内往往存在分离 ,这是总压恢复降低的主要原因 .试验表明在进气道出口的左上角存在低能量区 ,而数值计算显示在进口外下角处首先出现流动分离 。
A Caret inlet was studied by means of experiment and numerical simulation. Basic aerodynamic characteristics of the inlet at low and subsonic speeds were presented. The experimental as well as computational results revealed that flow separations may exist at match state of inlet/engine at low speeds due to the existence of large mass flow rate coefficients. It was the true mechanism causing the low total pressure recovery in the inlet as demonstrated. Experimental results show a low total pressure region being taken place at the upper left corner of the duct exit, which is matched with the results obtained by numerical computations showing that flow separations on set occurs at the low-outboard corner of inlet entrance and develop with no circumrotation.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2003年第6期512-515,共4页
Journal of Beijing University of Aeronautics and Astronautics
关键词
进气道
数值模拟
流动分离
Caret
Computer simulation
Pressure distribution
Subsonic aerodynamics
