|
[Sponsors] |
August 28, 2012, 09:34 |
RAE2822 transonic aerofoil
|
#1 |
New Member
Alexandru Stroe
Join Date: Dec 2011
Posts: 4
Rep Power: 14 |
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
|
|
January 28, 2013, 12:57 |
|
#2 |
New Member
Alexandru Stroe
Join Date: Dec 2011
Posts: 4
Rep Power: 14 |
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.
|
|
May 22, 2013, 12:55 |
|
#3 |
New Member
Join Date: Mar 2009
Posts: 1
Rep Power: 0 |
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 |
|
May 23, 2013, 04:05 |
|
#4 |
New Member
Alexandru Stroe
Join Date: Dec 2011
Posts: 4
Rep Power: 14 |
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.
|
|
May 27, 2013, 08:40 |
interesting
|
#5 | |
Member
|
Quote:
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".
__________________
practice makes perfect |
||
May 27, 2013, 09:04 |
|
#6 |
New Member
Alexandru Stroe
Join Date: Dec 2011
Posts: 4
Rep Power: 14 |
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 |
|
May 28, 2013, 03:35 |
|
#7 | |
Member
|
Quote:
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.
__________________
practice makes perfect |
||
May 28, 2013, 04:55 |
NACA 23012 results, transonic flow
|
#8 |
Member
|
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
__________________
practice makes perfect |
|
December 16, 2014, 03:19 |
RAE 2822 - Experimental measures
|
#9 |
New Member
Pierluigi Rossi
Join Date: Jul 2014
Location: Milan
Posts: 15
Rep Power: 11 |
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. |
|
February 6, 2015, 12:45 |
|
#10 | |
New Member
Boping M.
Join Date: Aug 2014
Location: China
Posts: 11
Rep Power: 11 |
Quote:
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 |
||
October 5, 2015, 00:04 |
|
#11 | |
New Member
Join Date: Jun 2013
Posts: 3
Rep Power: 12 |
Quote:
Regards, Ridwan |
||
December 24, 2015, 03:58 |
|
#12 |
New Member
Rui Wang
Join Date: Dec 2015
Posts: 1
Rep Power: 0 |
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 |
|
February 1, 2017, 15:28 |
did u manage to get it?
|
#13 | |
Member
Zack
Join Date: Dec 2015
Location: uk
Posts: 34
Rep Power: 10 |
Quote:
|
||
May 6, 2017, 05:10 |
|
#14 | |
New Member
Xu Yiming
Join Date: Jan 2017
Posts: 11
Rep Power: 9 |
Quote:
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 |
||
July 31, 2018, 20:02 |
|
#15 |
New Member
Manahara Manatunga
Join Date: Mar 2014
Posts: 15
Rep Power: 12 |
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
|
|
November 11, 2019, 13:31 |
Experimental data of RAE 2822
|
#16 |
New Member
Zhenkai Zhang
Join Date: Oct 2019
Posts: 3
Rep Power: 6 |
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 |
|
November 15, 2019, 04:51 |
|
#17 |
New Member
mohammed mahdi
Join Date: Jan 2010
Location: Sudan, Khartoum
Posts: 8
Rep Power: 16 |
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 |
|
February 25, 2020, 07:23 |
|
#18 | |
New Member
Wang Yifan
Join Date: Jan 2018
Posts: 4
Rep Power: 8 |
Quote:
|
||
|
|
Similar Threads | ||||
Thread | Thread Starter | Forum | Replies | Last Post |
Transonic rhoSimpleFoam Equations | eric.m.tridas | OpenFOAM | 3 | January 25, 2012 10:52 |
Transonic Dip & Phase lag | technophobe | Main CFD Forum | 0 | April 24, 2009 15:52 |
Compressible transonic airfoil RAE2822 simulation | Stefano | Siemens | 9 | June 21, 2006 10:47 |
Meshing an aerofoil with a plain flap | Fatou | FLUENT | 0 | November 15, 2005 14:24 |
2D Aerofoil Simulation | StudentAndrew | CFX | 10 | October 28, 2005 16:15 |