关键词: 流体喷射;矢量喷管;三维流;二次喷射;流动分布;数值仿真

Abstract: The Reynolds-averaged Navier-Stokes equations were solved numerically by Roe’s flux difference splitting scheme for three dimensional nozzle flow field with fluidic injection. The location of injector slot was at ahead slot or at behind slot. Ratio of injection pressurer was 0.75 - 2.0, ratio of injection flux was 2.5% - 10.0% , and the thrust vector angle ranged from 2.8 to 7.8. The results indicate that as the ratio of injection pressure and the ratio of injection flux increases, the thrust vector angle also increases . The location of injector slot has significant effects on the predicted thrust vector angle, and the behind slot injection can produce greater thrust vector angle than the ahead slot injection. The use of fluidic injection control clearly has significant potential to meet the challenges of aircraft thrust-vectoring technology.

Key words: Fluid injection;Vectoring nozzle;Three dimensional flow;Secondary injection;Flow distribution;Numerical simulation