空气动力学学报2011，Vol.29Issue(3)：257-263,7.
双下侧定几何二元混压式进气道的流场特征和气动性能分析
Flow pattern and performance of fixed-geometry two-dimensional mixed- compression supersonic inlets with 90° configuration at the venter of the missile
摘要
Abstract
The flow pattern and performance of fixed-geometry two-dimensional mixed-compression supersonic inlets with 90°configuration at the venter of the missile have been investigated by numerical simulation which has been validated by experimental data.Results indicate: 1 ) Under higher than started Math number of 2.25 within range of suitable backpressure, the terminal shocks can be stabilized at the convergence channels of the inlet because the aerodynamic throat was formed by boundary layer.2) With the increase of the free stream Mach number, the total pressure recovery coefficient decreases, while the mass flow ratio ascends gradually and maintains 1.0 when the oblique shocks attach the cowl lip.3 ) With the range of the angle of attack to a certainty, the total pressure recovery coefficient and the flow ratio increase.But after the inlet is not started, with the increase of the angle of attack, the total pressure recovery coefficient and the mass flow ratio have been little influenced.4) With the increase of yaw angle, the total pressure recovery coefficient of the two inlets are all decrease.关键词
航空/航天推进系统/冲压发动机/双下侧布局/二元进气道/数值仿真/流场特性/气动特性Key words
aerospace propulsion system/ ramjet/ twin-inlet 90° configurations at the renter/ two-dimensional supersonic inlet/ numerical simulation/ flow pattern/ aerodynamic performance分类
航空航天引用本文复制引用
谢旅荣,郭荣伟..双下侧定几何二元混压式进气道的流场特征和气动性能分析[J].空气动力学学报,2011,29(3):257-263,7.基金项目
国家863项目 （）
