摘要
为适应未来超声速巡航飞机动力系统的要求,作为一种可能的解决方案,本文对于一类来流为轴向超声速、出口为相对亚声速的高压比新概念风扇开展了研究,主要采用三维定常粘性数值方法对转子通道内部激波结构进行了初步探讨,根据流场分布构造了转子三维激波结构,为此类风扇气动设计提供了一定的依据。
To promote the performance of propulsion system of future supersonic cruising airplane, a kind of new concept fan which has axial supersonic incoming and subsonic exiting flow condition was presented and preliminarily explored with its 3D shock wave structure in the rotor passage through a 3D steady viscus Navier-Stokes code. The numerical results showed that there was a complicate 3D shock wave structure in the rotor passage.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2002年第6期699-702,共4页
Journal of Engineering Thermophysics
基金
国家重点基础研究发展规划项目(No.G1999022305)
