Performance evaluation, sensitivity analysis, and mitigating instabilities of Coanda effect-based flow control for a transonic jet: The investigation of shock effects

A flying object can be controlled in various ways. A specific flow control for a transonic jet has been proposed recently based on the Coanda effect and auxiliary flows. The present research uses experimental studies and numerical simulations to discuss and better understand the flow physics of this technique. First, the numerical simulations are validated based on experimental results. Then, a numerical simulation is used to determine various phenomena created in this flow, such as oblique shocks, Mach disks, barrel shocks, deflected shocks, and expansions and compressible fans. The results indicate that the thrust vector deflection is not significantly affected by nozzle sealing in the areas near the Coanda surface and connections with the body. Finally, considering the instabilities of this technique and the sensitivity of its performance to air sealing, a method is mentioned that will eliminate a significant part of its problems while maintaining the advantages of this technique.