CFD Online Logo CFD Online URL
www.cfd-online.com
[Sponsors]
Home > Forums > Software User Forums > ANSYS > FLUENT

Incorrect Cl and Cd data for a 3D airfoil

Register Blogs Members List Search Today's Posts Mark Forums Read

Reply
 
LinkBack Thread Tools Search this Thread Display Modes
Old   November 13, 2014, 10:13
Default Incorrect Cl and Cd data for a 3D airfoil
  #1
New Member
 
raina
Join Date: Oct 2014
Posts: 2
Rep Power: 0
araina85 is on a distinguished road
I am trying to model a 3D airfoil i.e. an infinite airfoil section to obtain and compare the lift and drag coefficients to that obtained from 2D. In principle, the 2D and 3D data should match. I am under-predicting the lift by ~50% and over-predicting drag by ~60%. I was using a k-w SST model for my simulations.

Given the incorrect results, I went back and simulated the 3D airfoil assuming no viscosity (inviscid solution). But even this solution provides me with a cl that is lower than the viscous experimental data.

Any ideas as to what I am doing wrong?

I could attach my case files if required.
araina85 is offline   Reply With Quote

Old   November 13, 2014, 12:31
Default
  #2
Senior Member
 
B_Kia
Join Date: May 2014
Location: Ir
Posts: 123
Rep Power: 9
HyperNova is on a distinguished road
Did you define the project area correctly ?
HyperNova is offline   Reply With Quote

Old   November 13, 2014, 14:09
Default
  #3
New Member
 
raina
Join Date: Oct 2014
Posts: 2
Rep Power: 0
araina85 is on a distinguished road
yes. I have a 1m chord with a 1m depth.
araina85 is offline   Reply With Quote

Reply

Tags
3d airfoil, drag coefficient, lift coefficient

Thread Tools Search this Thread
Search this Thread:

Advanced Search
Display Modes

Posting Rules
You may not post new threads
You may not post replies
You may not post attachments
You may not edit your posts

BB code is On
Smilies are On
[IMG] code is On
HTML code is Off
Trackbacks are Off
Pingbacks are On
Refbacks are On



All times are GMT -4. The time now is 13:50.