弹用混压式轴对称进气道开槽数值仿真  

Numerical Simulation of Flow in Axisymmetric Mixed-compression Supersonic Inlet with Cavity

作　　者：莫展[1] 王新月[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《计算机仿真》2008年第12期95-97,121,共4页Computer Simulation

摘　　要：为了提高定几何超声速混压式轴对称进气道的性能,应用在进气道不同位置开槽的方法,研究了在各级锥体上、进气道肩部、喉道下游分离区等不同位置开槽对进气道性能的影响;研究了多工况下锥面上开槽时进气道总压恢复系数、流量系数、冲压比和起动性能等产生的影响。研究表明锥面开槽将改变超声速进气道头锥上的压缩性能,从而提高了进气道高马赫数下的总压恢复系数与冲压比,同时能有效降低进气道的重量;在进气道肩部开槽能消除进气道肩部的分离;在进气道喉道下游分离区开槽能改善该位置处的分离。The paper investigates the performance of an axisymmetric supersonic inlet with cavities at the cone surface, the shoulder or the seporation position by numerical simulation. The performances such as total pressure recovery, the pressing ratio, the mass capture ratio, and the started Mach number are influenced by different positions of the cavities under inlet＇s different work conditions. The shock system is changed when the cavities are at different positions. The paper discusses the, performance disciplines of the inlet with different cavities. The surface cavities make the inlet＇s pressure recovery and the pressing ratio numbers are bigger than the inlet without cavities from Mach number 3.5 to Mach number 4. 5. The supersonic flow could be compressed by the cavity. The cavity at the separation position could make the separation area smaller.

关 键 词：超声速轴对称进气道 开槽 数值模拟 

分 类 号：V271.4[航空宇航科学与技术—飞行器设计]