采用数值模拟方法对涡扇发动机排气系统球面收敛二元矢量喷管的气动和红外辐射特性进行了研究,研究仅针对地面状态和俯仰偏转.结果表明:俯仰偏转角在小于20°范围内,俯仰偏转对排气系统推力系数和总压恢复系数的影响微弱,气动推力矢量角与俯仰偏转角几乎相等;由于气体的容积性热辐射特征,喷管俯仰偏转角的变化引起高温喷流红外辐射的方向性变化明显,喷管俯仰偏转时的热喷流在3~5μm波段红外辐射呈现一定幅度的增加;排气系统在3~5μm波段的红外辐射峰值随俯仰偏转角的增加而趋于减小,其出现位置小于俯仰偏转角;在大的俯仰偏转角下,排气系统在垂直探测平面上方的红外辐射较无矢量偏转情形有所降低,但在探测面下方却有明显的增强,导致另一个峰值的出现. The aerodynamic and infrared radiation characteristics of the spherical convergent binary vector nozzle of the exhaust system of a turbofan engine were studied by numerical simulation, and the results were only based on the ground state and the pitch deflection.The results show that the pitch angle is within the range of less than 20 °, The influence of pitch deflection on the thrust coefficient and total pressure recovery coefficient of the exhaust system is weak, and the aerodynamic thrust vector angle is nearly equal to the pitch deflection angle. Due to the volumetric thermal radiation characteristics of the gas, the variation of the nozzle pitch deflection angle causes the high-temperature jet infrared radiation , The infrared radiation in the 3-5 μm band increases with the increase of the amplitude of the infrared radiation in the jet pitch-deflection. The peak value of the infrared radiation of the exhaust system in the band of 3 ~ 5 μm tends to decrease with the increase of the pitch deflection angle Is smaller than the pitch deflection angle. Under the large pitch deflection angle, the infrared radiation of the exhaust system above the vertical detection plane is lower than that without vectorial deflection, but there is a significant enhancement below the detection plane, resulting in The emergence of another peak.