Paper Key : IRJ************990
Author: Hariom Patidar
Date Published: 03 Aug 2022
Abstract
A Super Sonic Nozzle is a duct that is compressed in the middle, forming a convergent-divergent shape like an hourglass. It accelerates flow to supersonic speeds, by exchanging the pressure and thermal energy into the kinetic energy. Super Sonic nozzles are widely employed in some types of steam turbines, supersonic jet engines, and rocket engine nozzles. Supersonic nozzle should have a shock-free and parallel steady flow. The substantial conditions of an ideal 2-dimensional, unfaltering stream may be communicated numerically by using the nonlinear differential condition of the potential flow. The strategy of characteristics may be a numerical detailing that could be utilized to dig up the answers to the previously mentioned potential flow, fulfilling the boundary conditions so the overseeing differential equations become ordinary differential equations.A scheme of the method of characteristics is utilized here for a 2-dimensional, C-D nozzle design. In applications like a rocket engine and supersonic aircraft, the length of the nozzle cannot be too large for less weight requirement, so we need to have the least possible length of the C-D nozzle. Hence, the method of designing a Minimum length C-D nozzle, for the designed exit Mach number with the steady flow at the diverging part of the nozzle, is presented in this thesis.