摘要
对具有圆转方过渡段的双喉道射流矢量喷管进行了设计建模和气动、红外辐射特性数值模拟计算。分析了其喷管射流注入角对喷管气动性能、矢量性能和红外辐射强度的影响。研究结果表明:射流注入角度为100度左右时,推力系数最大;次流降低了双喉道二元射流矢量喷管的全向红外辐射强度,推力矢量方位的辐射强度普遍更小;130°射流角时,双喉道射流矢量喷管红外辐射强度较小。
Design modeling, numerical simulation and calculation of aerodynamic and infrared radiation characteristics are conducted for the duplex-throat efflux vector nozzle with circle-to-rectangular transition portion. The paper analyzes the effect of nozzle efflux injection angle on the aerodynamic performance, vector performance and infrared radiation intensity. The results show that： the thralst coefficient is maximum at 100 degree injection angle; the secondary flow reduces the omni-directional infrared radiation intensity of duplex-throat two-directional efflux vector nozzle; especially infrared radiation intensity in the direction of thrust vector is generally smaller, and that of duplex-throat efflux vector nozzle is minimum at the 130 degree injection angle.
出处
《教练机》
2015年第1期16-23,共8页
Trainer
关键词
双喉道喷管
推力矢量
气动特性
逆向模特卡诺法
红外辐射强度
duplex-throat nozzle
thrust vector
aerodynamic characteristic
RMCM
infi＇ared radiation intensity
