OpenFOAM/C2/Supersonic-flow-over-a-wedge/English

Tutorial:Supersonic flow over a wedge using OpenFOAM

Script : Arvind N

Narration: Rahul Joshi

Keywords: Video tutorial,CFD,Wedge,Mach number,Compressible flows.

Visual Cue	Narration
Slide 1	Hello and welcome to the spoken tutorial on Supersonic flow over a wedge using OpenFOAM
Slide 2: Learning Objectives	In this tutorial I will show you how to solve a compressible flow problem of supersonic flow over a wedge how post process the results in paraView.
Slide 3: System Requirement	To record this tutorial I am using Linux Operating system Ubuntu version 10.04 OpenFOAM version 2.1.0 ParaView version 3.12.0
Slide 4 Prerequisites	To practice this tutorial a learner should have some basic knowledge of Compressible flows and Gas Dynamics
Slide 5 :	Let us now solve supersonic flow over a wedge using OpenFOAM and see the shock structure formed using paraview
Slide 5 :	The problem consists of a wedge with semi-angle of 15 degrees kept in a uniform supersonic flow
Inlet velocity 5m/s	Inlet velocity is 5 meters per second
Boundary conditions as shown in the figure	The boundary conditions are set as shown in the figure
Slide 6 : Solver	The type of solver I am using here is rhoCentralFoam
	It is a Density-based compressible flow solver It is based on central- upwind schemes of Kurganov and Tadmor
Switch to the Terminal by Ctrl+Alt+T	Open a command terminal to do this press ctrl +alt+ t keys simultaneously on your keyboard
	In the terminal type path for supersonic flow over a wedge
In command terminal: Type run and press enter Problem is already set in OpenFOAM	In the terminal Type 'run' and press enter
Type cd tutorial and press enter	Now type cd tutorial - Press Enter
Type cd compressible - Press Enter	cd compressible - Press Enter
Type cd rhoCentralFoam - Press Enter	cd rhoCentralFoam - Press Enter
Type cd wedge and press enter	cd wedge15Ma5 and press enter
	This is the name of the folder of supersonic flow over a wedge in rhoCentralFoam and press enter
Type ls	now type ls and press enter
	You will see three folders : 0,constant and system.
Type cd constant and press enter	Now open the blockMeshDict file, to do this type cd space constant and press enter
Type cd polyMesh and press enter	cd space polyMesh note that M here is capital and press enter
Type ls and press enter	Now type ls and press enter you can see the blockMeshDict file
Type gedit blockMeshDict and press enter	type gedit space blockMeshDict note that M and D here are capital and press enter
	let me drag this to the capture area scroll down
enter the data in vertices but it i already set up in the problem	In this you need to calculate the co-ordinates for the wedge This is already been calculated and set up in the problem
	The rest of the data remain the same
Boundary names similar to that in slide 5	In boundary patches the boundaries are set as shown in the figure
	Close the blockMeshDict file
type : cd .. (twice) and press enter wedge folder	in the command terminal type cd ..(dot dot) twice to return back to wedge folder
	Now Open the 0 folder
Type cd 0 and press enter	To do this type cd space 0 and press enter
type ls and press enter	type ls and press enter
	this contains initial boundary condition for pressure,velocity and Temprature
type cd .. and press enter	type cd .. (dot dot) and press enter
	Now we need to mesh the geometry
Mesh the geometry type: blockMesh	To do this in the command terminal type blockMesh and Press Enter Meshing has been done
Terminal : type paraFoam and press enter	Now to view the geometry in the terminal type paraFoam and press enter This will open the paraview window
Paraview window	On the left hand side of object inspector menu click APPLY
About wedge geometry	In this you can see the geometry is which is a rectangular section upstream and changes to a wedge downstream Close the paraview window
	Now run the solver 'rhoCentralFoam'
Terminal : rehoCentralFoam and press enter	To do this in the command terminal type rhoCentralFoam and Press Enter
Iterations in terminal window	The iterations running can be seen in the terminal window
	Iterations running will stop after it converges or at the end of the time step Now the solving has been done
open paraview	To visualise these results let us open the paraview window once again
type: paraFoam and press enter	In the command terminal type “paraFoam” and press Enter
Click APPLY in object inspector menu	Again on the left hand side of object inspector menu click APPLY
Solid geometry in drop down menu Select U	On the left side top in active variable control menu you will see a drop down menu showing solid color. Now click on it And change from solid color to capital U
Make the color legend ON	Now make the color legend ON by clicking on left hand side top of active variable control menu and make the color legend ON click on it
	On top of the paraview window you can see the VCR control Click on PLAY
In the paraview window	You can see the final results of U velocity
In object inspector menu	Now scroll down the properties in object inspector menu on left hand side Now click on display besides properties
Click on rescale to size	Scroll down and click on Rescale to Size
	You can see the final value of Velocity magnitude
Slect pressure in drop dwon menu (p)	Similarly you can select pressure You can see the final result of pressure Now close the paraview window
Calculate the Mach number in terminal type Mach	You can also calculate the Mach number for the flow To do this we can use the Openfoam utility by typing Mach in the command terminal
Type mach in terminal mach number for each time step	Type Mach in the command terminal Note that M here is capital and press enter You can see that Mach number is calculated for each time step
Open paraview window type paraFoam click APPLY	Now again open the paraview window By typing in the command terminal paraFoam and press enter click APPLY
In object inspector menu check the Ma check box change from solid color to Ma	scroll down 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
In VCR control click on play button make the color legend ON	In the VCR control menu click on PLAY and make the color legend ON
In paraview window	You can see the Mach number in the color legend and corresponding colours
Slide : For validation	Let me switch back to the slides The solved tutorial can be validated with exact solution available in basic books of Aerodynamics by John D Anderson
Slide ; Summary	In this tutorial we learnt: Solving a compressible flow problem Velocity and pressure contour for the wedge OpenFOAM utility for calculating the Mach number
Slide 9 : Assignment	Assignment: Vary the wedge angle between 10 ° to 15 ° to view the shock characteristic for the flow
Slide 10: About Spoken tutorials	The video available at this URL: http://spoken-tutorial.org/What_is_a_Spoken_Tutorial It summarizes the Spoken Tutorial project. If you do not have good bandwidth, you can download and watch it.
Slide 11: About Spoken tutorials	The Spoken Tutorial Project Team -Conducts workshops using spoken tutorials -Gives certificates to those who pass an online test -For more details, please write to us at contact@spoken-tutorial.org
Slide 12: Acknowledgement	Spoken Tutorials are part of Talk to a Teacher project, 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
About the contributor	This script has been contributed by Arvind M and this is Rahul Joshi from IIT BOMBAY signing off. Thanks for joining.

Contributors and Content Editors

Chandrika, DeepaVedartham, Nancyvarkey, Rahuljoshi