2D Contour Design and Analysis of the Divergent Portion of a Satellite Thruster Nozzle using MOC

This paper deals with the design of supersonic nozzles based on the theory of method of characteristics in two-dimensional regime. A MATLAB program was developed and utilized to compute the minimum length of the supersonic nozzle at the diverging section of the nozzle for the optimum Mach number at the nozzle exit with uniform flow. Numerical analysis is done and the solution is established for steady, in viscid, irrotational supersonic flow in two dimensions. An arbitrary shape is assumed for the converging section of the supersonic nozzle because of the rational assumption, the flow holds the consistency in the converging section. The design is focused on the diverging section of the nozzle. Citation: Veda Jose, Mar Athansius College of Engineering; Aneesh k johny ,Mar Athansius College of Engineering; Vinod Yeldho Baby ,Mar Athansius College of Engineering. "2D Contour Design and Analysis of the Divergent Portion of a Satellite Thruster Nozzle using MOC." Global Research and Development Journal For Engineering 25 2017: 162 - 168.