Abstract
Performance of propulsion system is the key parameter in getting efficient flying vehicles. The exhaust nozzle is highly important component of propulsion system, in order to improve nozzle performance understanding of geometrical parameters is mandatory. The nozzle design need optimization for various parameters like inlet, throat and exit width, but impact of inlet convergent angle and length have got less attention. In this research effect of convergent section length and angle of supersonic nozzle were analyzed by keeping same expansion ratio and boundary conditions. The numerical simulation was made on unstructured gird. The computational work is carried out on 2D axi-symmetric density based, coupled solver with viscous k SST turbulence model and linearized through implicit scheme. Study reveals that 28.5o inlet angle would give best result and maximum thrust force would be produced at this angle. From simulation results it was analyzed that flow behavior inside the nozzle is highly complex nature.
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