Thrust Augmentation in a Supersonic Nozzle

The CFD analysis of a convergent divergent nozzle has been conducted to understand the phenomena of the supersonic flow through various divergent angles and different throat to that of inlet diameter ratio. Numerical study has been accompanied using k-ε model at different divergence angle. Governing equations were solved by using the finite-volume method in ANSYS CFX software. The boundary conditions were quantified according to the available experimental information. The present project is designed at investigate supersonic flow at different divergence angle and different throat to that of inlet diameter ratio, the deviations in the parameters like the Mach number, static pressure, are being analysed and nozzle design will be optimized. Mach number is found to be increasing with increase in divergent angle there by obtaining an optimal divergent angle. A Computational Fluid Dynamics (CFD) software package, ANSYS CFX tool is used to simulation for compressible, viscous gas flow-field in different nozzle shapes. Here throat diameter to that of inlet diameter has been varied and analysis has been carried out. Based on the Mach number we are optimizing the geometry. Further optimized geometry has been analysed at different altitude. Modelling and meshing has been done through ICEM-CFD. Analysis has been done through CFX and results obtained through CFD-POST.