CFD Investigation in CD Nozzle at Different Convergence Angles and Constant Divergence Angle and Throat Diameter

In aircraft, mechanical, and other engineering applications, nozzles are the most widely utilized equipment. The nozzle is a device that allows the hot exhaust gases produced in the combustion chamber to be accelerated. Nozzle accelerates the flow to supersonic regimes to produce required thrust. This work presents computational approach made to investigate the flow behavior inside the CD nozzle by varying the convergence angle. The characteristics of converging half-angles on different performance parameters are quantitatively studied. In present work convergence angles ranging from 40,45,50 and 55 degrees is being used for investigation. To model the compressible flow of gas within the nozzle as well as its hot exhaust plumes, the k - epsilon analytical equation is used. Exhaust nozzle characteristics were computed and compared to existing empirical evidence to demonstrate the models' correctness. The nozzle model was created with SolidWorks software version (2013), and study will employ Ansys FLUENT software (18.1) to depict fluctuations in velocity, Mach number, pressure, and temperature contours, and the validated CFD process will be used to conduct the CFD investigation.