[stater]

Hi,

It's my first question in this forum and I hope a reply.
I'm trying to plot the pressure distribution around airfoil (just near the wall. Is there anyone who can help me to do that.
I'm using paraview and the results are obtained by OpenFOAM.
Thank your for your help

[haakon]

This was discussed yesterday: SampleDict Pressure Plot across a wing chord I hope that you find your answer there.

[msuaeronautics]

Stater,

An alternative method (compared to what's in that thread) is to just open the airfoil surface VTK file in Paraview and take a chordwise plane slice.

Once you've done this, open up the Spreadsheet View and select that slice in the small drop-down menu. Click File ---> Export Data (or something to that effect). This will export pressure at data points on that plane slice on the surface of the airfoil into a .csv file, which can be further manipulated.

Please let me know if you need any further help.

[stater]

Hi haakon and msuaeronautics,

thank you for yours helps.
Finally I preferred the Fimiya method's mentioned in Haakon tread, it was easy to doing it. However I have problem with method using sampleDict.
I put sampleDict in system directory and I launched OP, but at the end I don't know where to go to plot the pressure using gnuplot

My sampleDict is as follow

/*--------------------------------*- C++ -*----------------------------------*\
| ========= | |
| \\ / F ield | OpenFOAM: The Open Source CFD Toolbox |
| \\ / O peration | Version: 2.0.1 |
| \\ / A nd | Web: www.OpenFOAM.com |
| \\/ M anipulation | |
\*---------------------------------------------------------------------------*/
FoamFile
{
version 2.0;
format ascii;
class dictionary;
object sampleDict;
}
// * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //

setFormat gnuplot;

surfaceFormat raw;

fields
(
p
);

sets
(
TopAirfoil
{
type cloud;
axis x;
points ((0.0473 0.0168 0.000)(0.9452 0.2397 0.000));
}

bottomAirfoil
{
type cloud;
axis x;
points ((0.9452 0.2397 0.000)(0.0493 0.0090 0.000));
}
);

// ************************************************** ********************* //

Thinks again

[s.m]

Originally Posted by msuaeronautics

Stater,

An alternative method (compared to what's in that thread) is to just open the airfoil surface VTK file in Paraview and take a chordwise plane slice.

Once you've done this, open up the Spreadsheet View and select that slice in the small drop-down menu. Click File ---> Export Data (or something to that effect). This will export pressure at data points on that plane slice on the surface of the airfoil into a .csv file, which can be further manipulated.

Please let me know if you need any further help.

hi stater, thanks for explaning us, i have a question:
how should we take a chordwise plane slice?
thank you very much