|
[Sponsors] |
Comparison of experimental and CFD results for the VA-2 supercritical airfoil |
|
LinkBack | Thread Tools | Search this Thread | Display Modes |
March 18, 2010, 14:02 |
Comparison of experimental and CFD results for the VA-2 supercritical airfoil
|
#1 |
New Member
Join Date: Mar 2010
Posts: 2
Rep Power: 0 |
Dear Fluent users,
I am currently studying the supercritical airfoil VA-2 with Fluent in order to compare the results with some experimental data (drag coefficient, pressure distribution). However I have some big differences between my results and the experimental data. For my study, I am using: - Spalart-Allmaras viscous model - Pressure based solver - M=0.75 - angle of attack = 0.6° - Reynolds number = 6 millions My main worry is about the turbulent inlet I have to put in the boundary conditions (pressure far-field). When I am using the Turbulent intensity and Hydraulic diameter (I have found the values of the wind tunnel) I get a drag coefficient of 0.0205 instead of 0.0101. When I am usins Turbulent intensity and Turbulent length scale, I get a drag coefficient of 0.0134. I don't know how to explain this difference particularly for the first one. Moreover when I am looking at my pressure distribution, I get a weak shock and I am not supposed to get one according to experimental data. I hope it is enough clear as I am non-native English speaker. If you need any other information or graph, ask me!! Aurélien |
|
May 6, 2013, 10:44 |
|
#2 |
Member
Join Date: Oct 2012
Posts: 47
Rep Power: 14 |
hi
I am searching for experimental data for supercritical airfoil.can you send me your data? |
|
March 8, 2016, 15:15 |
|
#3 |
New Member
Amar Fayyad K.A
Join Date: Mar 2016
Posts: 1
Rep Power: 0 |
Hi,
Since the Mach Number you deal is 0.75 over a super-critical aerofoil such as VA 2, you should be considering density based solver rather than pressure based solver in order to accommodate compressibility effects. |
|
April 24, 2024, 11:39 |
Help
|
#4 |
New Member
wangshunshun
Join Date: Oct 2023
Posts: 1
Rep Power: 0 |
I want to have VA-2 airfoil geometry data.
|
|
Thread Tools | Search this Thread |
Display Modes | |
|
|
Similar Threads | ||||
Thread | Thread Starter | Forum | Replies | Last Post |
Is it worth it? | Jason Bardis | Main CFD Forum | 47 | July 27, 2011 05:52 |
CFD vs Experimetal Results for Aerofoil | aceofharts414 | Main CFD Forum | 0 | April 22, 2009 08:14 |
validation of CFD results | andy | FLUENT | 0 | June 13, 2007 14:55 |
HELP! Experimental & numerical results don't agree | Jenny Rollo | FLUENT | 5 | April 23, 2006 15:12 |
Experimental Results of flow over a cylinder | dhandapani.s | Siemens | 0 | August 25, 2003 07:12 |