Numerical study on a thermal response of the jet vane system in a rocket nozzle

The analysis of the heat transfer characteristics on the surface of jet vane needs to know ablation mechanism in a rocket engine. In this study, the distribution of heat transfer coefficient on the vane surface is calculated by means of the thermal boundary layer analysis for two dimension jet vane model. This method is only needed to get the free stream information around a vane and not required many fine meshes with large calculation time. User defined functions are inserted into a numerical code (FLUENT) for calculation of thermal boundary conditions. Some properties such as density, Mach number and heat transfer coefficient are plotted along the vane surface for different attack angles and several time steps. Also, the temperature contour inside vane is represented during the operation time. Finally, the heat transfer coefficient calculated by boundary layer integral method compares to that of using FLUENT solver itself.