Numerical Analysis of Cone Type Rocket Nozzle
Abstract- The basic principle of a rocket engine is based on the Newtonian third principle that “to every action there is an equal and opposite reaction”. A rocket engine is throwing mass in one direction and benefiting from the reaction that occurs in the other direction. The hot pressurized gas passing through the nozzle converted to a supersonic speed as the expansion takes place so that the heat energy of propelling the flow is maximally converted into directed kinetic energy. Because of this, it is an essential part of the modern rocket engine. Cone type nozzle is simple and easy to construct amongst the various type of rocket nozzles. The present work incorporates 2D axisymmetric flow analysis within the cone type nozzle, at design and off-design condition, by using computational fluid dynamic software GAMBIT 2.4.6 and FLUENT 6.3.26.Shear Stress Transport k-ω turbulence model has been chosen for flow analysis. The result shows the distribution of the Mach number, pressure, temperature and velocity inside the cone type rocket nozzle. FLUENT predictions are used to verify the isentropic flow assumption, and that the working fluid reached the user defined the desired exit Mach number. Good agreement in the area ratio and the exit Mach number were achieved.
Keywords - Rocket Nozzle, Cone type Nozzle, Numerical Analysis, Compressive Waves (Shock Wave)