Computational and experimental analysis of the flow field in shock vector control nozzle

In order to study the influencing factors for the efficiency of shock vector control system in solid rocket engine, and verify the accuracy of the numerical method, an experimental investigation has been conducted to determine the static pressure on the wall of the shock vector control axisymmetric nozzle. The complex inner flowfield of the nozzle was numerically simulated by solving three-dimensional average Reynolds Navier-Stokes equations using second-order precision Roe scheme and the k-ω shear stress transport two equations turbulent models. The structure of the flow-field of the vectoring nozzle, induced by the interaction of primary inflow and secondary inflow, and the distribution of the static pressure on the wall of different nozzle pressure ratio and secondary pressure ratio were analyzed and investigated. The results indicated that the computational results show good agreement with experimental data, which validates the veracity of numerical method; the static pressure differential on the circumference wall and the thrust vectoring efficiency increases with the decreasing of the nozzle pressure ratio and increasing of the secondary pressure ratio in some range.