为研究超音速分离线摆动喷管气动性能优势,采用数值仿真方法,分析其流动结构,并对摆角和分离线间隙距离的影响规律进行研究。结果表明,各摆角下超音速分离线摆动喷管矢量角放大系数均大于1;随着摆角增大,喷管轴向推力系数与矢量角放大系数快速下降,摆角为7°时,轴向推力系数为0.955,矢量角放大系数达1.19。另外,分离线间隙距离增大,喉衬后缘高压区大幅减小,喷管侧向力减小,矢量角放大系数下降。

A supersonic split line nozzle was numerically studied to estimate its aerodynamic advantages and obtain its flow structure and performance characteristics. Results indicate that, when the nozzle swing, the amplification factor can be greater than 1. With the increase of the swing angle, the axial thrust coefficient and amplification factor of the supersonic split line nozzle decrease obviously. When the swing angle is 7 degree, the axial thrust coefficient and amplification factor are 0.955 and 1.19, respectively. Moreover, as the distance of the split line gap increases, the high pressure zone, caused by the oblique shock, appear to drop considerably, and leading the amplification factor to decrease.