Numerical investigation of the fluidic injection angle effects on thrust vectoring

A computational investigation of the fluidic injection angle effects on fluidic thrust vectoring was conducted. Simulation of a two-dimensional convergent-divergent (2DCD) nozzle withshock-vector control method of fluidic injection for pitch vector control was performed with the computational fluid dynamics, using Spalart-Allmaras (S-A) one equation turbulence model. Nozzle design included fluidic variables and injection angle. The secondary flow was injected through a slot in the upper divergent wall. A nozzle pressure ratio (NPR) of 4.6.was assumed. Variable secondary pressure ratios (SPR) from 0.7 to 1.6 were investigated at Mw=0.05; which correspondeds to secondary mass flow rates of 4% to 10% of the primary mass flow rate. The effect of variable fluidic injection angle from 60° to 120° on pitch thrust vector angle and thrust vectoring efficiency were investigated. Computational results indicates that increasing SPR in all cases, increased pitch thrust vector angle and decreased thrust vectoring efficiency; also the greatest pitch thrust vector angle was achieved in the smaller fluidic injection angle.