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The distribution of heat flux of the combustor is particularly important for the thermal protection system of scramjet.A new method is presented for calculating the average heat flux through the wall temperature including the thermal response model,convergence criteria and control algorithms.Then the axial and circumferential distribution of the average heat flux could be calculated by using the method and the temperature which is measured in the experiments of Mach 6 and different equivalence ratios.And the reason about the heterogeneous distribution of the heat flux is obtained through the distribution.In addition,the rule of the combustion heat release which is useful for guiding the combustion and the design of the thermal protection system is also obtained by analyzing the distribution.