The Jet Ejector Thrust Vector Numerical Study

In this thesis, we introduced the recent development of the thrust-vectoring control (TVC) technique and it's application in the military jet aircrafts with high maneuverability. In more special, fluidic thrust-vectoring concept is described in more detail. Compared with conventional mechanical thrust-vectoring, the fluidic thrust-vectoring has some superiority respect to stealth and weight characteristics. To get the basic understanding of the influences on the thrust-vector angle and thrust-vectoring efficiency, a two-dimensional convergent-divergent(2DCD) nozzle with fluidic injection is simulated by solving Reynolds averaging N-S equations with flux difference-splitting scheme of Roe and Menter's k-Omega SST turbulence model. It is advanced in time with an implicit approximate-factorization method to obtain the steady solutions of the N-S equations. The computational results show that the thrust-vectoring angle is dependent on the freestream Mach number, nozzle pressure ratio(NPR), the position of the injection and secondary pressure ratio(SPR). From the computational results we can see that thrust-vectoring can be generated effectively by injecting fluid in the diverging section of the nozzle.