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

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| 00:07
 
| 00:07
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| In this tutorial, I will show you: * How to solve a '''compressible flow''' problem of '''supersonic flow over a wedge '''  
+
| In this tutorial, I will show you: * How to solve a '''compressible flow''' problem of '''supersonic flow over a wedge ''' How to postprocess the results in '''paraView'''.
−
How to postprocess the results in '''paraView'''.
+
  
 
|-
 
|-
 
| 00:18
 
| 00:18
−
| To record this tutorial, I am using:
+
| To record this tutorial, I am using:'''Linux Operating system Ubuntu''' version 10.04'''OpenFOAM''' version 2.1.0'''ParaView''' version 3.12.0
−
'''Linux Operating system Ubuntu''' version 10.04
+
−
'''OpenFOAM''' version 2.1.0
+
−
'''ParaView''' version 3.12.0
+
  
 
|-
 
|-
 
| 00:30
 
| 00:30
 +
| The tutorials were recorded using the versions specified in previous slide. Subsequently the tutorials were edited to latest versions. To install latest system requirements go to Installation Sheet
 +
 +
|-
 +
| 00:35
 
| To practice this tutorial, a learner should have some basic knowledge of '''Compressible flows''' and'''Gas Dynamics'''.
 
| To practice this tutorial, a learner should have some basic knowledge of '''Compressible flows''' and'''Gas Dynamics'''.
  
 
|-
 
|-
−
| 00:38
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| 00:43
 
| Let us now solve '''supersonic flow''' over a '''wedge''' using '''OpenFOAM''' and see the '''shock structure''' formed using '''paraview'''.
 
| Let us now solve '''supersonic flow''' over a '''wedge''' using '''OpenFOAM''' and see the '''shock structure''' formed using '''paraview'''.
  
 
|-
 
|-
−
| 00:47
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| 00:52
 
| The problem consists of a wedge with a '''semi-angle''' of 15 degrees kept in a uniform '''supersonic flow'''.
 
| The problem consists of a wedge with a '''semi-angle''' of 15 degrees kept in a uniform '''supersonic flow'''.
  
 
|-
 
|-
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| 00:55
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| 01:00
 
|The Inlet velocity is 5 meters per second.
 
|The Inlet velocity is 5 meters per second.
  
 
|-
 
|-
−
| 01:00
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| 01:05
 
| The '''boundary condition'''s are set as shown in the figure.
 
| The '''boundary condition'''s are set as shown in the figure.
  
 
|-
 
|-
−
| 01:05
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| 01:10
 
| The type of '''solver''' I am using here is '''rhoCentralFoam'''.
 
| The type of '''solver''' I am using here is '''rhoCentralFoam'''.
  
 
|-
 
|-
−
| 01:10
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| 01:15
 
| It is a '''Density'''-based '''compressible flow solver'''. It is based on '''central- upwind''' '''schemes of Kurganov and Tadmor'''.
 
| It is a '''Density'''-based '''compressible flow solver'''. It is based on '''central- upwind''' '''schemes of Kurganov and Tadmor'''.
  
 
|-
 
|-
−
| 01:21
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| 01:26
 
| Open a '''command terminal '''. To do this, press '''ctrl +alt+ t''' keys simultaneously on your keyboard.
 
| Open a '''command terminal '''. To do this, press '''ctrl +alt+ t''' keys simultaneously on your keyboard.
  
 
|-
 
|-
−
| 01:28
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| 01:33
 
| In the command terminal, type the path for '''supersonic flow''' over a '''wedge'''.
 
| In the command terminal, type the path for '''supersonic flow''' over a '''wedge'''.
  
 
|-  
 
|-  
−
|01:35
+
|01:40
 
|In the terminal, type "run" and press '''Enter'''.
 
|In the terminal, type "run" and press '''Enter'''.
  
 
|-
 
|-
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| 01:40
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| 01:45
−
| '''cd space tutorials''' and press '''Enter'''.
+
| '''cd space tutorials''' and press '''Enter'''.'''cd space compressible ''' and press '''Enter'''.'''cd space rhoCentralFoam''' and press '''Enter'''.
−
'''cd space compressible ''' and press '''Enter'''.
+
−
'''cd space rhoCentralFoam''' and press '''Enter'''.
+
  
 
|-
 
|-
−
|02:02
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|02:07
 
| '''cd space wedge15Ma5'''
 
| '''cd space wedge15Ma5'''
  
 
|-
 
|-
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| 02:13
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| 02:18
 
| This is the name of the folder of '''supersonic flow''' over the wedge in '''rhoCentralFoam''' and press '''Enter'''.
 
| This is the name of the folder of '''supersonic flow''' over the wedge in '''rhoCentralFoam''' and press '''Enter'''.
  
 
|-
 
|-
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| 02:21
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| 02:26
 
| Now, type "ls" and press '''Enter'''.
 
| Now, type "ls" and press '''Enter'''.
  
 
|-
 
|-
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| 02:24
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| 02:29
 
| You will see three folders: '''0, constant''' and '''system'''.
 
| You will see three folders: '''0, constant''' and '''system'''.
  
 
|-
 
|-
−
| 02:29
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| 02:34
 
| Now, open the '''blockMeshDict file'''. To do this,  
 
| Now, open the '''blockMeshDict file'''. To do this,  
  
 
|-
 
|-
−
|02:34
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|02:39
 
|type '''cd space constant''' and press '''Enter'''.
 
|type '''cd space constant''' and press '''Enter'''.
  
 
|-
 
|-
−
| 02:41
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| 02:46
 
| '''cd space polyMesh''' note that 'M' here is capital and press '''Enter'''.
 
| '''cd space polyMesh''' note that 'M' here is capital and press '''Enter'''.
  
 
|-
 
|-
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| 02:49
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| 02:54
 
| Now type "ls" and press '''Enter'''. You can see the '''blockMeshDict file'''.
 
| Now type "ls" and press '''Enter'''. You can see the '''blockMeshDict file'''.
  
 
|-
 
|-
−
| 02:54
+
| 02:59
 
| To view the '''blockMeshDict''' file, type '''gedit space blockMeshDict'''. Note that 'M' and 'D' here are capital, press '''Enter'''.
 
| To view the '''blockMeshDict''' file, type '''gedit space blockMeshDict'''. Note that 'M' and 'D' here are capital, press '''Enter'''.
  
 
|-
 
|-
−
| 03:08
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| 03:13
 
| Let me drag this to the '''capture area''', scroll down.
 
| Let me drag this to the '''capture area''', scroll down.
  
 
|-
 
|-
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| 03:14
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| 03:19
 
| In this, you need to calculate the co-ordinates for the wedge.
 
| In this, you need to calculate the co-ordinates for the wedge.
  
 
|-
 
|-
−
| 03:20
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| 03:25
 
| This has been already calculated and set up in the problem.
 
| This has been already calculated and set up in the problem.
  
 
|-
 
|-
−
| 03:23
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| 03:28
 
| The rest of the data remains the same.
 
| The rest of the data remains the same.
  
 
|-
 
|-
−
|03:29
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|03:34
 
| In '''boundary patches''',  boundaries are set as shown in the figure.  
 
| In '''boundary patches''',  boundaries are set as shown in the figure.  
  
 
|-
 
|-
−
| 03:33
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| 03:38
 
| Close  '''blockMeshDict''' file.
 
| Close  '''blockMeshDict''' file.
  
 
|-
 
|-
−
| 03:36
+
| 03:41
 
| In the command terminal, type '''cd space ..(dot dot)''' twice to return back to '''wedge''' folder.
 
| In the command terminal, type '''cd space ..(dot dot)''' twice to return back to '''wedge''' folder.
  
 
|-
 
|-
−
| 03:45
+
| 03:50
 
| Now open the 0 (zero) folder.
 
| Now open the 0 (zero) folder.
  
 
|-
 
|-
−
| 03:51
+
| 03:56
 
| To do this, type '''cd space 0''' and press '''Enter'''.
 
| To do this, type '''cd space 0''' and press '''Enter'''.
  
 
|-
 
|-
−
| 03:58
+
| 04:03
 
| Type "ls" and press '''Enter'''.
 
| Type "ls" and press '''Enter'''.
  
 
|-
 
|-
−
| 04:02
+
| 04:07
 
| This contains the initial boundary condition for pressure, velocity and Temperature.  
 
| This contains the initial boundary condition for pressure, velocity and Temperature.  
  
 
|-
 
|-
−
| 04:10
+
| 04:15
 
| Type '''cd space .. (dot dot)''' and press '''Enter'''. Now we need to '''mesh''' the geometry.
 
| Type '''cd space .. (dot dot)''' and press '''Enter'''. Now we need to '''mesh''' the geometry.
  
 
|-
 
|-
−
| 04:19
+
| 04:24
 
| To do this, in the '''command terminal''', type "blockMesh" and press '''Enter'''. '''Meshing''' has been done.
 
| To do this, in the '''command terminal''', type "blockMesh" and press '''Enter'''. '''Meshing''' has been done.
  
 
|-
 
|-
−
| 04:32
+
| 04:37
 
| Now, to view the geometry- in the  command terminal,  type "paraFoam" and press '''Enter'''. This will open the '''paraview''' window.
 
| Now, to view the geometry- in the  command terminal,  type "paraFoam" and press '''Enter'''. This will open the '''paraview''' window.
  
 
|-
 
|-
−
| 04:45
+
| 04:50
 
| On the left hand side of '''object inspector''' menu, click '''APPLY'''.
 
| On the left hand side of '''object inspector''' menu, click '''APPLY'''.
  
 
|-
 
|-
−
| 04:53
+
| 04:58
 
| In this, you can see the geometry in which the rectangular  section '''upstream'''  changes to a '''wedge downstream'''. Close the '''paraview''' window.
 
| In this, you can see the geometry in which the rectangular  section '''upstream'''  changes to a '''wedge downstream'''. Close the '''paraview''' window.
  
 
|-
 
|-
−
| 05:05
+
| 05:10
 
| Now, '''run''' the '''solver''' '''rhoCentralFoam'''.  
 
| Now, '''run''' the '''solver''' '''rhoCentralFoam'''.  
  
 
|-
 
|-
−
| 05:11
+
| 05:16
 
| To do this, in the command terminal, type "rhoCentralFoam" and press '''Enter'''.
 
| To do this, in the command terminal, type "rhoCentralFoam" and press '''Enter'''.
  
 
|-
 
|-
−
| 05:20
+
| 05:25
 
| The '''iterations''' running can be seen in the terminal window.
 
| The '''iterations''' running can be seen in the terminal window.
  
 
|-
 
|-
−
| 05:24
+
| 05:29
 
| '''Iterations''' running will stop after it converges or at the end of the time steps. Now, the solving has been done.
 
| '''Iterations''' running will stop after it converges or at the end of the time steps. Now, the solving has been done.
  
 
|-
 
|-
−
| 05:34
+
| 05:39
 
| To visualize these results, let us open the '''paraview''' window once again.
 
| To visualize these results, let us open the '''paraview''' window once again.
  
 
|-
 
|-
−
| 05:40
+
| 05:45
 
| In the '''command terminal''', type “paraFoam” and press Enter.
 
| In the '''command terminal''', type “paraFoam” and press Enter.
  
 
|-
 
|-
−
| 05:49
+
| 05:54
 
| Again on the left hand side of '''object inspector''' menu, click '''APPLY'''.
 
| Again on the left hand side of '''object inspector''' menu, click '''APPLY'''.
  
 
|-
 
|-
−
| 05:56
+
| 06:01
 
| 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'.
 
| 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'.
  
 
|-
 
|-
−
| 06:14
+
| 06:19
 
| 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.
 
| 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.
  
 
|-
 
|-
−
| 06:28
+
| 06:33
 
| On top of the '''Paraview''' window, you can see the '''VCR control'''. Click on '''PLAY'''.
 
| On top of the '''Paraview''' window, you can see the '''VCR control'''. Click on '''PLAY'''.
  
 
|-
 
|-
−
| 06:37
+
| 06:42
 
| You can see the final results of '''U velocity'''.
 
| You can see the final results of '''U velocity'''.
  
 
|-
 
|-
−
| 06:42
+
| 06:47
 
| Now, scroll down the  properties in '''object inspector menu''' on the left hand side. Now click on '''Display''' besides '''Properties'''.
 
| Now, scroll down the  properties in '''object inspector menu''' on the left hand side. Now click on '''Display''' besides '''Properties'''.
  
 
|-
 
|-
−
| 06:56
+
| 07:01
 
| Scroll down and click on '''Rescale to Size'''. You can see the final value of '''Velocity, magnitude'''.
 
| Scroll down and click on '''Rescale to Size'''. You can see the final value of '''Velocity, magnitude'''.
  
 
|-
 
|-
−
| 07:05
+
| 07:10
 
| Similarly, you can select '''pressure'''. You can see the final result of '''pressure'''. Now, close the '''paraView''' window.
 
| Similarly, you can select '''pressure'''. You can see the final result of '''pressure'''. Now, close the '''paraView''' window.
  
 
|-
 
|-
−
| 07:16
+
| 07:21
 
| 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.  
 
| 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.  
  
 
|-
 
|-
−
| 07:26
+
| 07:31
 
| Type '''Mach'''.
 
| Type '''Mach'''.
  
 
|-
 
|-
−
|07:29
+
|07:34
 
| Note that 'M' here is capital and press '''Enter'''. You can see that '''Mach number''' is calculated 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.
  
 
|-
 
|-
−
| 07:36
+
| 07:41
 
| Now, again open the '''paraview ''' window by typing in the command terminal "paraFoam" and press '''Enter'''.
 
| Now, again open the '''paraview ''' window by typing in the command terminal "paraFoam" and press '''Enter'''.
  
 
|-
 
|-
−
| 07:48
+
| 07:53
 
| Click '''APPLY''', scroll down. In '''volume fields''', check the 'Ma' box and again click '''APPLY'''.
 
| Click '''APPLY''', scroll down. In '''volume fields''', check the 'Ma' box and again click '''APPLY'''.
  
 
|-
 
|-
−
| 08:04
+
| 08:09
 
| On top of the''' active variable control''' menu, click on '''Solid Color''' and change it to 'Ma'.
 
| On top of the''' active variable control''' menu, click on '''Solid Color''' and change it to 'Ma'.
  
 
|-
 
|-
−
| 08:11
+
| 08:16
 
| In the '''VCR control''' menu, again click on '''PLAY''' and make the '''color legend 'ON''''.
 
| In the '''VCR control''' menu, again click on '''PLAY''' and make the '''color legend 'ON''''.
  
 
|-
 
|-
−
| 08:21
+
| 08:26
 
| You can see the '''Mach number''' in the''' color legend''' and the corresponding colours.
 
| You can see the '''Mach number''' in the''' color legend''' and the corresponding colours.
  
 
|-
 
|-
−
| 08:29
+
| 08:34
 
| We notice here that when the '''wedge''' is kept in '''supersonic flow''', it produces a '''shock''' across which the flow properties like temprature, pressure  
 
| We notice here that when the '''wedge''' is kept in '''supersonic flow''', it produces a '''shock''' across which the flow properties like temprature, pressure  
 
and density drastically change.
 
and density drastically change.
  
 
|-
 
|-
−
|08:43
+
|08:48
 
| 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.
 
| 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.
  
 
|-
 
|-
−
| 08:55
+
| 09:00
 
| In this tutorial, we learnt: * '''Solving a compressible flow problem'''
 
| In this tutorial, we learnt: * '''Solving a compressible flow problem'''
−
'''Velocity''' and '''pressure contour''' for the wedge and  
+
 
−
  '''OpenFOAM utility''' for calculating the '''Mach number'''.
+
'''Velocity''' and '''pressure contour''' for the wedge and  '''OpenFOAM utility''' for calculating the '''Mach number'''.
  
 
|-
 
|-
−
| 09:06
+
| 09:11
 
| As an Assignment, vary the wedge angle between 10 ° to 15 °  to view the''' shock characteristic''' for the flow.
 
| As an Assignment, vary the wedge angle between 10 ° to 15 °  to view the''' shock characteristic''' for the flow.
  
 
|-
 
|-
−
| 09:14
+
| 09:19
−
| This brings us to the end of the tutorial. Watch the video available at this URL:
+
| This brings us to the end of the tutorial. Watch the video available at this URL: http://spoken-tutorial.org/What_is_a_Spoken_Tutorial  
−
http://spoken-tutorial.org/What_is_a_Spoken_Tutorial  
+
  
 
|-
 
|-
−
| 09:21
+
| 09:26
 
| It summarizes the Spoken Tutorial project. If you do not have good bandwidth, you can download and watch it.  
 
| It summarizes the Spoken Tutorial project. If you do not have good bandwidth, you can download and watch it.  
  
 
|-
 
|-
−
| 09:28
+
| 09:33
−
| The Spoken Tutorial Project team:
+
| The Spoken Tutorial Project team: Conducts workshops using spoken tutorials  
−
Conducts workshops using spoken tutorials  
+
 
−
Gives certificates to those who pass an online test.
+
Gives certificates to those who pass an online test. For more details, please write to us at '''contact@spoken-tutorial.org'''
−
For more details, please write to us at '''contact@spoken-tutorial.org'''
+
  
 
|-
 
|-
−
| 09:41
+
| 10:07
 
| '''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.
 
| '''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
+
More information on the same is available at the following URL link: http://spoken-tutorial.org/NMEICT-Intro
  
 
|-
 
|-
−
| 09:56
+
| 10:20
 
| This script has been contributed by Arvind M and this is Rahul Joshi from '''IIT Bombay''', signing off. Thanks for joining.
 
| This script has been contributed by Arvind M and this is Rahul Joshi from '''IIT Bombay''', signing off. Thanks for joining.
  
 
|}
 
|}

Latest revision as of 12:29, 11 April 2019

Time Narration
00:01 Hello and welcome to the spoken tutorial on Supersonic flow over a wedge using OpenFOAM.
00:07 In this tutorial, I will show you: * How to solve a compressible flow problem of supersonic flow over a wedge How to postprocess the results in paraView.
00:18 To record this tutorial, I am using:Linux Operating system Ubuntu version 10.04OpenFOAM version 2.1.0ParaView version 3.12.0
00:30 The tutorials were recorded using the versions specified in previous slide. Subsequently the tutorials were edited to latest versions. To install latest system requirements go to Installation Sheet
00:35 To practice this tutorial, a learner should have some basic knowledge of Compressible flows andGas Dynamics.
00:43 Let us now solve supersonic flow over a wedge using OpenFOAM and see the shock structure formed using paraview.
00:52 The problem consists of a wedge with a semi-angle of 15 degrees kept in a uniform supersonic flow.
01:00 The Inlet velocity is 5 meters per second.
01:05 The boundary conditions are set as shown in the figure.
01:10 The type of solver I am using here is rhoCentralFoam.
01:15 It is a Density-based compressible flow solver. It is based on central- upwind schemes of Kurganov and Tadmor.
01:26 Open a command terminal . To do this, press ctrl +alt+ t keys simultaneously on your keyboard.
01:33 In the command terminal, type the path for supersonic flow over a wedge.
01:40 In the terminal, type "run" and press Enter.
01:45 cd space tutorials and press Enter.cd space compressible and press Enter.cd space rhoCentralFoam and press Enter.
02:07 cd space wedge15Ma5
02:18 This is the name of the folder of supersonic flow over the wedge in rhoCentralFoam and press Enter.
02:26 Now, type "ls" and press Enter.
02:29 You will see three folders: 0, constant and system.
02:34 Now, open the blockMeshDict file. To do this,
02:39 type cd space constant and press Enter.
02:46 cd space polyMesh note that 'M' here is capital and press Enter.
02:54 Now type "ls" and press Enter. You can see the blockMeshDict file.
02:59 To view the blockMeshDict file, type gedit space blockMeshDict. Note that 'M' and 'D' here are capital, press Enter.
03:13 Let me drag this to the capture area, scroll down.
03:19 In this, you need to calculate the co-ordinates for the wedge.
03:25 This has been already calculated and set up in the problem.
03:28 The rest of the data remains the same.
03:34 In boundary patches, boundaries are set as shown in the figure.
03:38 Close blockMeshDict file.
03:41 In the command terminal, type cd space ..(dot dot) twice to return back to wedge folder.
03:50 Now open the 0 (zero) folder.
03:56 To do this, type cd space 0 and press Enter.
04:03 Type "ls" and press Enter.
04:07 This contains the initial boundary condition for pressure, velocity and Temperature.
04:15 Type cd space .. (dot dot) and press Enter. Now we need to mesh the geometry.
04:24 To do this, in the command terminal, type "blockMesh" and press Enter. Meshing has been done.
04:37 Now, to view the geometry- in the command terminal, type "paraFoam" and press Enter. This will open the paraview window.
04:50 On the left hand side of object inspector menu, click APPLY.
04:58 In this, you can see the geometry in which the rectangular section upstream changes to a wedge downstream. Close the paraview window.
05:10 Now, run the solver rhoCentralFoam.
05:16 To do this, in the command terminal, type "rhoCentralFoam" and press Enter.
05:25 The iterations running can be seen in the terminal window.
05:29 Iterations running will stop after it converges or at the end of the time steps. Now, the solving has been done.
05:39 To visualize these results, let us open the paraview window once again.
05:45 In the command terminal, type “paraFoam” and press Enter.
05:54 Again on the left hand side of object inspector menu, click APPLY.
06:01 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'.
06:19 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.
06:33 On top of the Paraview window, you can see the VCR control. Click on PLAY.
06:42 You can see the final results of U velocity.
06:47 Now, scroll down the properties in object inspector menu on the left hand side. Now click on Display besides Properties.
07:01 Scroll down and click on Rescale to Size. You can see the final value of Velocity, magnitude.
07:10 Similarly, you can select pressure. You can see the final result of pressure. Now, close the paraView window.
07:21 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.
07:31 Type Mach.
07:34 Note that 'M' here is capital and press Enter. You can see that Mach number is calculated for each time step.
07:41 Now, again open the paraview window by typing in the command terminal "paraFoam" and press Enter.
07:53 Click APPLY, scroll down. In volume fields, check the 'Ma' box and again click APPLY.
08:09 On top of the active variable control menu, click on Solid Color and change it to 'Ma'.
08:16 In the VCR control menu, again click on PLAY and make the color legend 'ON'.
08:26 You can see the Mach number in the color legend and the corresponding colours.
08:34 We notice here that when the wedge is kept in supersonic flow, it produces a shock across which the flow properties like temprature, pressure

and density drastically change.

08:48 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.
09:00 In this tutorial, we learnt: * Solving a compressible flow problem

Velocity and pressure contour for the wedge and OpenFOAM utility for calculating the Mach number.

09:11 As an Assignment, vary the wedge angle between 10 ° to 15 ° to view the shock characteristic for the flow.
09:19 This brings us to the end of the tutorial. Watch the video available at this URL: http://spoken-tutorial.org/What_is_a_Spoken_Tutorial
09:26 It summarizes the Spoken Tutorial project. If you do not have good bandwidth, you can download and watch it.
09:33 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

10:07 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

10:20 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

DeepaVedartham, PoojaMoolya, Pratik kamble, Sandhya.np14

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