Abstract
The present study focuses on the numerical investigation of the Mach 1.86 supersonic jet from the 2-D convergent-divergent nozzle for NPR (nozzle pressure ratio) values of 5 to 8 with a step size of one, covering the overexpansion, correct expansion and the underexpansion conditions using Realizable k-ε turbulence model under the steady state condition. The computational model is constructed using the design modeler of ANSYS 16.0 workbench. The structured grids are generated into the ICEM module of the ANSYS workbench and the fluid flow analysis is done by FLUENT solver. The plot of non-dimensional total pressure along the jet centerline with respect to the non-dimensional downstream distance of the nozzle exit along the jet centerline identify the extent of jet mixing. The contours of Mach number with different NPRs visualize the effects of shock cells and shock strength prevail into the jet flow field due the favorable and adverse pressure gradients at the nozzle exit.
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