Supersonic / Hypersonic Nozzle Change Than The Hot Surface And Numerical Simulation

In recent years, the most of new fighters and strategic missiles require fly with supersonic or hypersonic speed, and this make a lot of researchers think much of this kinds of phenomena. The design and computation of the hypersonic nozzle have scientific and practical value to solve these problems.With high temperature and high pressure in nozzle of wind tunnel, the effect of variable specific heat on nozzle design must be considered. An algorithm based on characteristics method with variable specific heat was developed to solve this problem. The results with variable specific heat were compared with constant specific heat. A large number of design, analysis and calculation have verified the accuracy of the method.To prove the accuracy of the Mach number, and the parameter homogeneity of the design nozzle' s exit, CFD calculate has carried on the design results. Under the condition of supersonic and hypersonic flow, and a certain range of temperature, and Mach number, the conclusion of the influence of specific heat to nozzle design is drawn.The results show that to design a Supersonic/Hypersonic nozzle of wind tunnel must consider the effect of variable specific heat, which gives reference to nozzle and wind tunnel design.