View source for OpenFOAM/C2/Supersonic-flow-over-a-wedge/English-timed

{|border=1 
| '''Time'''
| '''Narration'''

|-
| 00:01
| Hello and welcome to the spoken tutorial on '''Supersonic flow over a wedge using OpenFOAM'''

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| 00:07
| In this tutorial I will show you How to solve a '''compressible flow''' problem of '''supersonic flow over a wedge ''' How to post process the results in '''paraView'''.

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| 00:18
| To record this tutorial I am using''' Linux Operating system Ubuntu version 10.04'''
'''OpenFOAM version 2.1.0'''
'''ParaView version 3.12.0'''

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| 00:30
| To practice this tutorial a learner should have some basic knowledge of '''Compressible flows''' and'''Gas Dynamics'''

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| 00:38
| Let us now solve '''supersonic flow''' over a '''wedge''' using '''OpenFOAM''' and see the '''shock structure''' formed using '''paraview'''

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| 00:47
| The problem consists of a wedge with '''semi-angle of 15 degrees''' kept in a '''uniform supersonic flow'''

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| 00:55
|The Inlet velocity is '''5 meters per second'''

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| 01:00
| The '''boundary condition'''s are set as shown in the figure

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| 01:05
| The type of solver I am using here is '''rhoCentralFoam'''

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| 01:10
| It is a '''Density'''-based '''compressible flow solver''' It is based on '''central- upwind''' '''schemes of Kurganov and Tadmor '''

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| 01:21
| Open a '''command terminal ''' to do this press '''ctrl +alt+ t''' keys '''simultaneously''' on your keyboard

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| 01:28
| In the command '''terminal''' type path for '''supersonic flow''' over a '''wedge'''

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|01:35
|In the terminal Type ''''run' and press enter'''

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| 01:40
|  '''cd tutorial - ''' and Press Enter  '''cd compressible - ''' and Press Enter  '''cd rhoCentralFoam - ''' and Press Enter

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|02:02
| '''cd wedge15Ma5 '''

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| 02:13
| This is the name of the folder of '''supersonic flow''' over a wedge in '''rhoCentralFoam''' and press enter'''

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| 02:21
| Now type''' ls''' and press enter

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| 02:24
| You will see '''three folders''' : '''0,constant and system.'''

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| 02:29
| Now open the '''blockMeshDict file''',to do this 

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|02:34
|type '''cd '''space '''constant''' and press enter

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| 02:41
| '''cd '''space '''polyMesh''' note that '''M''' here is capital and press enter

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| 02:49
| Now type '''ls''' and press enter you can see the '''blockMeshDict file'''

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| 02:54
| To view'''blockMeshDict file''' type '''gedit''' space''' blockMeshDict'''  note that '''M and D '''here are capital press enter

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| 03:08
| let me drag this to the '''capture area''' scroll down

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| 03:14
| In this you need to '''calculate''' the '''co-ordinate''' for the wedge

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| 03:20
| This has been already '''calculated''' and set up in the problem

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| 03:23
| The rest of the data remains the same

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|03:29
| In '''boundary patches'''  boundaries are set as shown in the figure 

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| 03:33
| Close  '''blockMeshDict file'''

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| 03:36
| in the '''command terminal''' type '''cd ..(dot dot)''' '''twice'''  to return back to '''wedge folder'''

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| 03:45
| Now Open the '''0 folder '''

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| 03:51
| To do this type '''cd '''space''' 0 and press enter'''

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| 03:58
| '''Type ls and press enter'''

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| 04:02
| This contains the initial boundary condition for '''pressure,velocity and Temperature''' 

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| 04:10
| Type '''cd .. (dot dot)''' and press enter.Now we need to '''mesh the geometry'''

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| 04:19
| To do this in the '''command terminal''' type '''blockMesh''' and Press Enter '''Meshing''' has been done

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| 04:32
| Now to view the geometry in the ''' command terminal ''' type '''paraFoam''' and press enter This will open the '''paraview''' window

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| 04:45
| On the left hand side of '''object inspector menu''' click '''APPLY'''

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| 04:53
| In this you can see the '''geometry''' in which the '''rectangular'''  '''section upstream'''  changes to a '''wedge downstream''' Close the '''paraview''' window

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| 05:05
| Now run the solver ''''rhoCentralFoam'''' 

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| 05:11
| To do this in the '''command terminal''' type '''rhoCentralFoam''' and Press Enter

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| 05:20
| The '''iterations''' running can be seen in the '''terminal window'''

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| 05:24
| '''Iterations running''' will stop after it '''converges '''or at the end of the time step Now the''' solving''' has been done

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| 05:34
| To '''visualise''' these results let us open the '''paraview window''' once again

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| 05:40
| In the '''command terminal''' type “'''paraFoam” '''and press Enter

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| 05:49
| Again on the left hand side of '''object inspector menu click '''APPLY'''

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| 05:56
| On the left hand 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'''

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| 06:14
| Now make the '''color legend ON''' by clicking on the left hand side top of '''active variable control menu''' and make the '''color legend ON''' '''click on it'''

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| 06:28
| On top of the '''Paraview window''' you can see the '''VCR control''' Click on '''PLAY'''

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| 06:37
| You can see the final results of '''U velocity'''

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| 06:42
| Now scroll down the  '''properties''' in '''object inspector menu''' on the left hand side Now click on '''display''' besides '''properties'''

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| 06:56
| Scroll down and click on '''Rescale to Size''' You can see the final value of '''Velocity magnitude'''

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| 07:05
| Similarly you can select '''pressure'''You can see the final result of '''pressure''' Now close the '''paraview window'''

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| 07:16
| 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 '''

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| 07:26
| Type '''Mach'''

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|07:29 
| Note that '''M''' here is '''capital''' and press enter.You can see that '''Mach number''' is calculated for each time step

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| 07:36
| Now again open the '''paraview window'''.By typing in the '''command terminal paraFoam'''and press enter

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| 07:48
| Click '''APPLY''' scroll down.In '''volume fields''' '''Check''' the '''Ma''' box and again click '''APPLY'''

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| 08:04
| On top of the''' active variable control menu''' click on '''Solid Color''' and change it to '''Ma'''

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| 08:11
| In the '''VCR control''' menu again click on '''PLAY''' and make the '''color legend ON'''

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| 08:21
| You can see the '''Mach number''' in the''' color legend''' and '''corresponding colours'''

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| 08:29
| We notice here that when the wedge is kept in supersonic flow it produce a shock across which the flow properties like temprature, pressure 
and density drastically changes

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|08:43
| Now 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'''

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| 08:55
| In this tutorial we learnt: '''Solving a compressible flow problem'''
'''Velocity''' and '''pressure contour''' for the wedge
'''OpenFOAM utility''' for calculating the '''Mach number'''

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| 09:06
| As an Assignment Vary the '''wedge angle between 10 ° to 15 ° ''' to view the''' shock characteristic''' for the flow

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| 09:14
| This bring us to the end of tutorial watch The video available at this URL: http://spoken-tutorial.org/What_is_a_Spoken_Tutorial 

|-
| 09:21
| It summarizes the Spoken Tutorial project. If you do not have good bandwidth, you can download and watch it. 

|-
| 09:28
| 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

|-
| 09:41
| Spoken Tutorials project is  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

|-
| 09:56
| This script has been contributed by Arvind M and this is Rahul Joshi from IIT BOMBAY signing off.Thanks for joining.

|}