Hybrid method for jet vane thermal analysis in supersonic nozzle flow

The thermal analysis of a jet vane system was conducted by the hybrid method of Computational Fluid Dynamics (CFD) and a boundary layer analysis. The correct physical and thermal properties for different materials were assumed, including their changes with temperature. The potential flow around a jet vane and the transient heat conduction in it were simulated while the heat flux on a vane surface was calculated with the analytic method for the thermal boundary layer. It was seen that both heat-transfer coefficient and recovery temperature had high values on a leading edge and they gradually decreased to the trailing edge along the lateral surface. The lower lateral surface showed a higher transfer coefficient and it seemed to be related to the higher compressible effect on it. The results showed that the vane nose part is heated quickly and the thermal protection effect of heat resisting skin is also confirmed.