Effect of aerodynamic parameters of main and secondary flow path on fluidic thrust vectoring

A numerical investigation was presented to simulate the flow field resulting from transverse jet injection through the divergent flap of a 2D convergent divergent nozzle for thrust vector. Based on CFD technology, the two dimensional flow field structures of 2D convergent divergent nozzle with fluidic injection for thrust vector were conducted. Simulations were computed with free stream Mach number 0.3 to 1.2, with scheduled nozzle pressure ratios (from 13.89 to 4.5), and secondary to primary total pressure ratios (from 1.0 to 0.4). The numerical results indicate that nozzle pressure ratios and secondary pressure ratios have important effects on thrust vector. The free stream Mach number decreases thrust vector performance. The thrust vector decreases with increasing nozzle pressure ratios. As injection pressure ratio increases, thrust vectoring also increases.