VMFL046

VMFL046
Supersonic Flow with Normal Shock in a Converging Diverging Nozzle

Overview

Reference F. M. White. Fluid Mechanics. 3rd Edition. McGraw-Hill Book Co., New York, NY. 518-531. 1994.

Solver Ansys Fluent

Physics/Models Compressible flow in supersonic regime, Normal shock

Input File

VMFL046_supersonic.cas

Project Files Link to Project Files Download Page

Test Case

Supersonic flow in a CD nozzle is modeled. The maximum Mach number is 2.2. A normal shock is formed in the divergent section. Mach number distribution in the nozzle is compared with analytical solution for nozzle flow.

Figure 116: Flow domain

Material Properties	Geometry	Boundary Conditions
Density: Ideal Gas Viscosity: 1.7894 x 10^-5 kg/m-s	Length of the nozzle = 2m Exit-to-throat area ratio = 3	Inlet Relative Pressure 200 kPa Inlet Total Temperature = 500 K Wall temperature = 328 K Outlet Relative Pressure (gauge) = 75 kPa

Material Properties

Geometry

Boundary Conditions

Density: Ideal Gas

Viscosity: 1.7894 x 10^-5 kg/m-s

Length of the nozzle = 2m

Exit-to-throat area ratio = 3

Inlet Relative Pressure 200 kPa

Inlet Total Temperature = 500 K

Wall temperature = 328 K

Outlet Relative Pressure (gauge) = 75 kPa

Analysis Assumptions and Modeling Notes

The flow is steady. The flow is modeled as laminar.

Results Comparison for Ansys Fluent

Figure 117: Comparison of Mach Number Along Center Line of the Nozzle With Analytical Solution