Abstract: An experimental investigation for the aerodynamic effects of fluidic injection in a two-dimensional,convergent-divergent(2DCD) nozzle has been conducted.Simulations were performed at static conditions of a single fluidic injection port with variable injection angles(60°,90° and 120°)at a relative position of x/xl=0.688,with the scheduled nozzle pressure ratios(NPR,from 4.5 to 13.89) and secondary to primary total pressure ratios(SPR) from 0.4 to 1.0.Results indicated a pressure rise on the nozzle wall centerline.It validated that the nozzle thrust vectoring angle and thrust coefficient change with different NPRs,SPRs and injection angles.

Key words: Fluidic thrust vectoring;Shock vectoring control;Vector angle

摘要： 以二元收扩喷管为对象,开展了基于二次流喷射的流体推力矢量技术研究。基于试验研究,得到了不同喷管落压比、不同的二次流总压比和不同的二次流喷射角度多种工况下的喷管上下壁面中心线压力分布规律以及喷管壁面油流分布图。通过对不同工况下参数变化规律分析,给出了基于二次流喷射的流体推力矢量喷管的主次流气动参数及几何参数对流体推力矢量喷管流场结构和性能影响的关联关系。从试验和分析结果可以看出,喷管落压比、二次流总压比和二次流喷射角度等喷管的主次流气动几何参数对基于流体推力矢量喷管参数变化有明显的影响。

关键词: 流体推力矢量;激波控制;矢量角