A computational investigation of the aerodynamic effects on fluidic thrust vectoring was conducted. Simulations of a two-dimensional convergent-divergent nozzle with shock-vector control method of fluidic injection for pitch vector control was performed with CFD, using Spalart-Allmaras one equation turbulence model. A static freestream condition (M = 0,05) at Mach numbers from M = 0,3 to 1,2, with nozzle pressure ratios of 4,6 and secondary to primary total pressure ratios of 0,7 were assumed. The aerodynamic penalty to thrust vector angle ranged from 3,9 degrees with M = 1,2 freestream condition to 1,08 degrees with M = 0,3 freestream condition, (compared to the same nozzle pressure ratios with static freestream conditions). Results indicate that the freestream flow decreases vectoring performance and thrust efficiency, compared to static (wind-off) condition.

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