Week 2 - Converging diverging nozzle

Aim: Study on Converging-Diverging nozzle.

Introduction: Converging-diverging nozzles are used in various aplications but most importantly in rocket engines. The combustion gasses escape and are accelerated to supesonic speeds to generate enough thrust that it lifts the whole weight to space. 

The setup is meshed using face meshing Quads to generate a structured mesh. This mesh has around 92000 elements.

Named selection is as follows: 

Nozzle wall : wall

Inlet: pressure inlet

Outlet: pressure outlet

Axis: Axis (For Axisymmetric simulation)

Setup: For the purpose of this simulation a 2 equation - k-epsilon (standard) model is used. As the flow is compressible the density based approach is used. Further for the BC's pressure inlet with 101325Pa is initializes and for the outlet (Pressure outlet) 2753.77Pa is used. The operating conditions is set to 0Pa.

Result:

Contour

Plots

Conclusion:

The simulation has been conducted successfully and the Mach number distribution along the nozzle shows when the flow is supersonic. The contours also show us the shock formation ad how the Mach numer, pressure and temperature varies along it.