Difference between revisions of "OpenFOAM/C2/Supersonic-flow-over-a-wedge/English"

how to solve a compressible flow problem of supersonic flow over a wedge

how post process the results in paraView.

System Requirement

I am using Linux Operating system Ubuntu version 10.04

OpenFOAM version 2.1.0

ParaView version 3.12.0

Prerequisites

Compressible flows and

Gas Dynamics

see the shock structure formed using paraview

with semi-angle of 15 degrees kept in a

uniform supersonic flow

It is based on central- upwind schemes of Kurganov and Tadmor

to do this press ctrl +alt+ t keys simultaneously on your keyboard

Type run and press enter

Problem is already set in OpenFOAM

and press enter

to do this

type cd space constant and press enter

note that M here is capital

and press enter

you can see the blockMeshDict file

note that M and D here are capital

and press enter

scroll down

This is already been calculated and set up in the problem

wedge folder

type cd ..(dot dot) twice

to return back to wedge folder

cd space 0 and press enter

type: blockMesh

type blockMesh and Press Enter

Meshing has been done

type paraFoam and press enter

This will open the paraview window

section upstream and changes to a wedge downstream

Close the paraview window

type rhoCentralFoam and Press Enter

terminal window

or

at the end of the time step

Now the solving has been done

paraview window once again

type “paraFoam” and press Enter

object inspector menu click APPLY

Select U

you will see a drop down menu showing solid color.

Now click on it

And change from solid color to capital U

by clicking on left hand side top of active variable control menu

and make the color legend ON

click on it

Click on PLAY

properties in object inspector menu on left hand side

Now click on display besides properties

You can see the final result of pressure

Now close the paraview window

in terminal type Mach

To do this we can use the Openfoam utility

by typing Mach in the command terminal

mach number for each time step

Note that M here is capital and press enter

You can see that Mach number is calculated for each time step

type paraFoam

click APPLY

By typing in the command terminal paraFoam

and press enter

click APPLY

check the Ma check box

change from solid color to Ma

In volume fields Check the Ma box and click APPLY

On top of active variable control menu click on Solid Color

and change it to Ma

make the color legend ON

and make the color legend ON

and corresponding colours

The solved tutorial can be validated with exact

solution

available in basic books of Aerodynamics by John D Anderson

Solving a compressible flow problem

Velocity and pressure contour for the wedge

OpenFOAM utility for calculating the Mach number

Vary the wedge angle between 10 ° to 15 °

to view the shock characteristic for the flow

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Acknowledgement

It is supported by the National Mission on Education through ICT, MHRD, Government of India.

More information on the same is available at the following URL link http://spoken-tutorial.org/NMEICT-Intro

and this is Rahul Joshi from IIT BOMBAY signing off.

Thanks for joining.