Fluidic Thrust-Vector Control of Supersonic Jet Using Coflow Injection

摘要

An investigation on operating parameters and dynamic characteristics of a FTVC system using a coflow control technique was studied experimentally and numerically. The results of numerical simulations were found to be fairly comparable with experimental results. Jet-deflection angle and pressure distribution of the divergent nozzle surface were measured as the ratio of control flow to main-flow pressures. The maximum deflection angle was found to increase linearly with the pressure ratio in a range of between 0.1 and 0.4. This observation implies that the control efficiency will be maximized at typical pressure ratios. Shocks appear in the control-flow exit and divergent wall as the control-flow pressure increases, which limits the jet-deflection angle. Axial thrust increases linearly with the control pressure increase at different main-jet pressures. The response to control-flow pressure in terms of vertical thrust may be in the control zone, outside of the control zone, or in the saturation zone. Thus, the optimum PR should be found near the boundary between the control zone and the saturation zone. That range is from PR 0.1 to 0.3.