[icedevill]

Hi. I am currently trying to simulate the flow over a rae2822 aerofoil. This is a transonic flow and from what I've read in the forum one of the suggested solvers is sonicFoam. The mesh was build using gmsh and I've adapted the data in the 0 folder to best suit my configuration. The initial conditions are found http://www.grc.nasa.gov/WWW/wind/valid/raetaf/raetaf04/raetaf04.html . The problem is that my Cp pressure distribution is nothing near of the original experiment results. I have attached my 0, system and constant folder if this could help. Also i attached a chart of the distribution of the pressure. Thank you in advance

[icedevill]

After much stress and searching around and help from others i got my simulation to work. The results are almost the same as other RAE2822 experiments, the only problem is that the shock is not where it is supposed to be. I attached a picture for reference. If anyone needs the case files, i will post them here. Also if you got any ideas about the shock, feel free to share them.

[Corretelli]

I suspect a discrepancy between the case described in the NASA website
http://www.grc.nasa.gov/WWW/wind/val.../raetaf04.html
and the wind tunnel study. The boundary conditions (Mach 0.729, alpha = 2.31 degrees) seems not to correspond to any experimental results in the AGARD report.

Please see case #6 in the table on page 191 of:
Cook, P.H., M.A. McDonald, M.C.P. Firmin, "Aerofoil RAE 2822 - Pressure Distributions, and Boundary Layer and Wake Measurements," Experimental Data Base for Computer Program Assessment, AGARD Report AR 138, 1979.

(I do not recall where I downloaded the report some years ago....)

The boundary conditions on the another part of the NASA website do seem to match case #6 in the AGARD report.
http://www.grc.nasa.gov/WWW/wind/val...af/raetaf.html

Mach 0.725, alpha = 2.92 degrees

Good luck; I don't know if you are still checking this forum, but I hope this helps others who are doing validation.

- Corretelli

[icedevill]

Indeed, the boundary conditions are different. I will simulate with the new values and maybe i will get an improvement. Thank you for your observations.

[skeptik]

Originally Posted by icedevill

Indeed, the boundary conditions are different. I will simulate with the new values and maybe i will get an improvement. Thank you for your observations.

Hi.

I wait for your further simulations. I do airfoil at M>>0.3 too but it's NACA 23012 and i really interesting about your results.

But i have several questions about your case cause i didn't see mesh (there is empty polyMesh in the archive).

Which size is your domain?

It seems that you have small simulation time, so the solution is not "stationary".

[icedevill]

I will attach an archive with what i did so far. The mesh was build using airfoilmesh2, a python script created by someone. The lengths of the domain, specified in the input script are:

-10 X_back control domain
5 X_front control domain
-5 Y_down control domain
5 Y_up control domain .

About the time: The deltaT in my controlDict file was the biggest i could find without crushing my simulation with an error. From what i read, finding the right deltaT is a matter of trial and error. Currently it is 4e-08, if i were to push it to 4e-07 for example, the simulation would crush. As a physical time i let it run for a couple of days as a single processor case.

Right now i am a bit caught between work and writing my dissertation, but i hope i will come with the new simulation results soon.

The archive is http://www.megafileupload.com/en/fil...e-diz-zip.html

[skeptik]

Originally Posted by icedevill

-10 X_back control domain
5 X_front control domain
-5 Y_down control domain
5 Y_up control domain .

About the time: The deltaT in my controlDict file was the biggest i could find without crushing my simulation with an error. From what i read, finding the right deltaT is a matter of trial and error. Currently it is 4e-08, if i were to push it to 4e-07 for example, the simulation would crush. As a physical time i let it run for a couple of days as a single processor case.

I mean endTime of your simulation, not timeStep.

If you have domain size about 15 m, and U approx 240 m/s, you need endTime approx 0.06. But i think it would be better to set 0.12 or higher just wait till Cx or Cy becomes constant.

[skeptik]

What i've got about my airfoil (exp and Fluent data were extracted from article, but it's in russian. originally exp data from TZAGI report)

M06_rhocentral.jpg

So there present oscillations, they were caused by second order schemes. I'll simulate it on upwind later.

The differences in p fields are showed here:

upwind
firstOrder.jpg

linear limited 1
secondOrd.jpg

also i will share my results obtained with sonicFoam, but later

[PierluigiRossi]

Dear all,

can someone send to me the following technical memorandum:

Cook, P.H., M.A. McDonald, M.C.P. Firmin, "Aerofoil RAE 2822 - Pressure Distributions, and Boundary Layer and Wake Measurements," Experimental Data Base for Computer Program Assessment, AGARD Report AR 138, 1979.

My email address follows:
kevin.kurany89@gmail.com

Thanks in advance.

[BopngMa]

Originally Posted by PierluigiRossi

Dear all,

can someone send to me the following technical memorandum:

Cook, P.H., M.A. McDonald, M.C.P. Firmin, "Aerofoil RAE 2822 - Pressure Distributions, and Boundary Layer and Wake Measurements," Experimental Data Base for Computer Program Assessment, AGARD Report AR 138, 1979.

My email address follows:
kevin.kurany89@gmail.com

Thanks in advance.

Hello, have anyone sent you the AGARD Report? In my stimulation result, the
position of the shock wave also meet with the data of the experiment data. I want to check the report to find out the problems. Thanks

[rfadlika]

Originally Posted by icedevill

After much stress and searching around and help from others i got my simulation to work. The results are almost the same as other RAE2822 experiments, the only problem is that the shock is not where it is supposed to be. I attached a picture for reference. If anyone needs the case files, i will post them here. Also if you got any ideas about the shock, feel free to share them.

Hi Alexandru Stroe,I am trying to run naca 0012 using sonicFoam, but I have no idea how to run using sonic Foam. Would you like to tell me if there is any tutorial?

Regards,

Ridwan

[tjuwangrui]

Hello,I am trying to simulate the flow over a rae2822 aerofoil(Mach 0.729, alpha = 2.31 degrees),but the solution never satisfies the experimental data in NASA website，so I want to try another initial condition .
Cook, P.H., M.A. McDonald, M.C.P. Firmin, "Aerofoil RAE 2822 - Pressure Distributions, and Boundary Layer and Wake Measurements," Experimental Data Base for Computer Program Assessment, AGARD Report AR 138, 1979.
I also need the paper,but I never found it because of the long time.
Do you ever find it?If possible,would you mind sending it to me?thanks in advance.
tjuwangui@tju.edu.cn

[ZakBristol]

Originally Posted by PierluigiRossi

Dear all,

can someone send to me the following technical memorandum:

Cook, P.H., M.A. McDonald, M.C.P. Firmin, "Aerofoil RAE 2822 - Pressure Distributions, and Boundary Layer and Wake Measurements," Experimental Data Base for Computer Program Assessment, AGARD Report AR 138, 1979.

My email address follows:
kevin.kurany89@gmail.com

Thanks in advance.

Did you get it, and if yes would you be able to send it to me?

[ousoweak]

Originally Posted by icedevill

Hi. I am currently trying to simulate the flow over a rae2822 aerofoil. This is a transonic flow and from what I've read in the forum one of the suggested solvers is sonicFoam. The mesh was build using gmsh and I've adapted the data in the 0 folder to best suit my configuration. The initial conditions are found http://www.grc.nasa.gov/WWW/wind/valid/raetaf/raetaf04/raetaf04.html . The problem is that my Cp pressure distribution is nothing near of the original experiment results. I have attached my 0, system and constant folder if this could help. Also i attached a chart of the distribution of the pressure. Thank you in advance

hi icedevill

I am doing the same validation simulation with RAE2822，can you post your final case here or send it to me？Thank you~

Yiming

Email：xuyimingmail@foxmail.com

[manahara]

I am trying to carry out a similar simulation in sonicFoam. I was wondering if you could reshare the case files with me, so I can understand how you went about setting up your simulation. The Megaupload link is no longer working. Thank you

[Scramjetdk]

For anyone who is looking for the "Cook, P.H., M.A. McDonald, M.C.P. Firmin, "Aerofoil RAE 2822 - Pressure Distributions, and Boundary Layer and Wake Measurements," Experimental Data Base for Computer Program Assessment, AGARD Report AR 138, 1979." can click the link below.

https://turbmodels.larc.nasa.gov/Bradshaw/d2/f8621.txt

[momahadi30]

I want to know the setup of the transonic solver in OpenFOAM for RAE 2822 airfoil
could anyone suggest a typical procedure for the running of the model

[YI Fan]

Originally Posted by Scramjetdk

For anyone who is looking for the "Cook, P.H., M.A. McDonald, M.C.P. Firmin, "Aerofoil RAE 2822 - Pressure Distributions, and Boundary Layer and Wake Measurements," Experimental Data Base for Computer Program Assessment, AGARD Report AR 138, 1979." can click the link below.

https://turbmodels.larc.nasa.gov/Bradshaw/d2/f8621.txt

Thanks for your sharing. But I can't find any data in this txt file. Is it a content of a database? Can you tell me how to use this link?