Experimental Investigations on Transient Flow and Heat Transfer Characteristics of Rp-3 at Supercritical Pressure

A hypersonic vehicle, its flight state is changeable, which is often related to the heat load change of chamber wall. Thermal and flow response characteristics during flight state change are investigated in this research experimentally by utilizing the electrically heat experiment system. It is revealed that the response time of flow and heat transfer due to step perturbation is longer than that of perturbation, and the response time decreased as the initial temperature increases when the temperature of the fuel is lower than the critical temperature. Once the temperature is higher than the critical temperature, the response time began to increase as the initial temperature increase. A 3D transient model is adopted to help to explain this phenomenon. The results indicate that the reason for the characteristics is the weakening of heat diffusion near the wall due to heat transfer deterioration. This conclusion is beneficial to the regulation of the coolant