CFD Analysis of Conical Nozzle for Mach 3 at Various Angles of Divergence with Fluent Software

Abstract —Numerical study has been conducted to understand the gas flows in a conical nozzle at different degree of angle using 2 dimensional axi-symmetric models, which solves the governing equations by a control volume method. The nozzle geometry co-ordinates are taken by using of method of characteristics which usually de signed for De-Laval nozzle. The present study is aimed at investigating the supersonic flow in conical nozzle for Mach 3 at various degree of angle. The throat diameter and exit diameter is same for all nozzles. The flow is simulated using Fluent software. The flow parameters, like pressure ratio, Area of nozzle exit ratio, and the Mach number of the flow at the nozzle exit is defined prior to the simulation. The result shows the variation in the Mach no., pressure ratio. For 40 angles the Mach number at exit is very low compared to other nozzles and the turbulence in tensity is very high for 160 at exit and it is nearly 3.045e+05. While when the angle is 80 the mach number at nozzle exit is 2.91 and same as 120 angle but an angle 160 it gives the mach number at nozzle exit is 2.92 and it is lowest at an angle 40. The degree of angle for conical nozzle can be large as 12 to 18 degree maximum so for maximum thrust we can go with 120 or 160 conical nozzle.