Design anatomization & numerical simulation of nozzle with exit deflection angle in scramjet

Supersonic Combustion jet engine is an engine where the combustion of the fuel inside the chamber happens at a supersonic flow velocity. Analysis is finished within the domain of the whole nozzle from entry to all the way further to exit part with Fixed Angle. A basic divergent nozzle design is considered and the moderation is done at the mid-section throughout the exit part by fixing the angles at the mid-section as per the enlargement zone proceeds up to exit. One angle is determined to get betterment inside the diffusion part of the nozzle and computational analysis is substantiated with Computational Fluid dynamics tool ANSYS fluent. Solving the density-based Navier Stokes equation and simulation is performed to obtain the numbers of pressure, temperature, density, and Mach no. by assuming the flow in the nozzle and fluid in the domain follows the ideal gas laws. Numerical analysis (MATLAB) is performed and the value of pressure, temperature, density, at every section of the divergent nozzle is calculated and compare both numerical and computational analysis to validate results.