Determination of Optimum Parameter Space of a Fluidic Thrust Vectoring System based on Coanda Effect Using Gradient-Based Optimization Technique

In the realm of aviation, jet propulsion systems serve to provide enhanced maneuverability and make sure that aircraft thrust is accurately precisely regulated during take-off landing operations. The movement aerodynamic control surfaces (flaps, slats, elevators, ailerons, spoilers, wing attachments) determines mobility practically all types. Recognized as dependable components in aviation world for tasks, these are being replaced by fluidic vectoring (FTV) systems, especially small unmanned aerial vehicles (UAVs) short or vertical aircraft. FTV system capable directing any preferred direction without need movable components. This paper numerically examines utilizing computational fluid dynamics (CFD) an optimization technique based on gradients understand physics Coanda effect systems. research employs gradient-based nozzle design order optimize parameter space different velocity ratios (VR) calculating moment around upper surface, which used represent deflection angle. context, four surface-pintle pair designs VRs produced. shows significant improvement configurations, results reveal output parameters successfully delay separation system's surface. Finally, optimum suggestions tested at various VRs, most efficient proper recommended parameters.