effects of divergence angle on moveable nozzle performance in thrust vector control system

in this paper, by numerical simulation of gas flow, effects of divergence angles on the amplification factor, side force and thrust vector magnitude of a moveable nozzle with supersonic split line have been investigated. the study is conducted for constant exit to throat area ratio and the location of the split line is also constant. the finite volume method with second order upwind scheme for spatial discretization and ausm method for flux splitting have been used in numerical solution of the equations. it was observed that for two different deviation angles, the results of rng k-ε turbulence model are in good agreement with experimental data. results also show that by increasing the divergence angle of the nozzle, the amplification factor, side force and thrust vector magnitude will decrease.