FLUIDIC INJECTION ANGLE IMPACT ON THRUST VECTORING USING COMPUTATIONAL FLUID DYNAMICS ANALYSIS

As shock vectoring evolved as a major option of thrust vector control in applications such as jet engine exhaust systems, the computational study (with the validation of experimental data) of injecting the secondary flow into the divergent section of convergent-divergent nozzle has become an attractive option to investigate its optimum performance by increasing the number of secondary injection ports with variation in injection angles. This has led us toward the use of multiple injection ports with varying injection angles for the current study. To perform the simulation of internal flow in the nozzle, a finite volume-based implicit computational fluid dynamics solver was used. The study aims to see the response of the injection angle on the pitch thrust vector using shock vector control. One equation turbulence model of Spalart-Allmaras was used for its precision and robustness, and its need for less computational time. Nozzle performance has been studied at nozzle pressure ratios of 4 and 6. The secondary pressure ratio varies as 0.4, 0.7, and 1. A comparative study of different configurations of multiple injection ports has been done at different injection angles. Shifting of injection slot from nozzle exit to near throat decreases the thrust vectoring capability of the nozzle. The injection angle varies from 60° to 120° concerning the flow direction in the nozzle. Increment in the injection angle has a significant increasing effect on the pitch thrust vector angle.