Possibilities of the fluidic thrust vector control of a supersonic rocket nozzle have been investigated in the framework of the CNES program Perseus for small satellite launcher. Cold flow experiments are performed in the hypersonic wind tunnel EDITH on several nozzle types and configurations. The complex three dimensional flow field generated by the supersonic cross-flows in these test nozzles is examined. Valuable experimental data is confronted and compared with the results of numerical simulations performed using the FANS solver of the code CPS C. Test case nozzle models are numerically simulated for experimental conditions and then further investigated for additional thrust vectoring parameters. Effects which characterize the nozzle and thrust vectoring performances are depicted. The study indicates that with moderate secondary to primary mass-flow-rate ratios, ranging around 5%, it is possible to achieve pertinent vector side force. It also reveals effects of injector geometry and positioning on the shock vector control system and nozzle performances.