Desingn of Variable Specific Heat Capacity for Hyporsonic Wind-Tunnel Nozzle

Supersonic and Hypersonic Wind-Tunnel nozzle are designed using Computational Fluid Dynamics.With high temperature and speed in nozzle,the effect of variable specific heat on nozzle design must be considered.A algorithm based on characteristics method with variable specific heat was developed to solve this problem.The problems of intercross of characteristics is solved in Hypersonic flow.Supersonic and Hypersonic Wind-Tunnel nozzle of Mach number to 7 are designed.The results show that to design a Supersonic/Hypersonic nozzle must consider the effect of variable specific heat,and it gives reference to nozzle design.This method is extremely accurate and easy to use.The final nozzle design is obtained either by doing a boundary layer correction or by using this inviseid design as the starting point for a viscous design optimization based on computational fluid dynamics.