Experiment And Simulation Investigation Of Scramjet Nozzle

The airframe and engine highly integration nature of hypersonic vehicle results in the asymmetry and cowl adjustable characters of the scramjet nozzle. In this paper, experimental and computational methods were introduced to study the characters of scramjet nozzle and to guide the design.About numerical simulations, at first the numerical results were compared with the experimental data published by NASA to prove the feasibility of the numerical method on the simulation of scramjet nozzle in hypersonic free stream. Equality design method was used in numerical simulations, and multiobjective optimization method was used to design the scramjet nozzle configuration. Then the nozzle was simulated to study the variation of its performance under different nozzle pressure ratios, flow conditions and with different configurations of the cowl. Through the analysis of the configuration of Scramjet nozzle flow field, some design methods of scramjet nozzle and the characteristics of its performance variation were found.About the experiment, these experiments were conducted in the free stream wind tunnel, and vitiated air heater was used to simulate the high altitude flow condition. Scramjet nozzle was installed at the exit of the combustor. Experimental data was collected by measuring the wall pressure.