Effect of Geometric Parameters on Steady-State Supersonic Film Cooling of the Basic Conical Rocket Nozzle

The current study proposes simulation results of supersonic film cooling of rocket nozzle by varying the geometric parameters. The study reveals that as the width of the injector opening for coolant injection was altered, the temperature variation trend near the walls differed based on the extent to which the width was increased or decreased. The results captured are shown in upcoming sections of this work. The second parameter varied was the angle of injection, where the variation of the cooling temperature after the injection point and the turbulence variation as a function of axial length were mainly focused. The temperature, turbulence, pressure, and density variation are also shown by varying the above parameters as a function of the axial length of the nozzle. The fluid used for primary and secondary flows was the air with different inlet and outlet pressures and temperatures as boundary conditions.