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

Problems with generated results of 3D wing analysis

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

Reply
 
LinkBack Thread Tools Search this Thread Display Modes
Old   March 12, 2010, 10:37
Default Problems with generated results of 3D wing analysis
  #1
New Member
 
Chong Shao ming
Join Date: Mar 2010
Posts: 1
Rep Power: 0
Shaoming is on a distinguished road
Hi all,

I am using Fluent to analyse a typical 3D wing problem under low Re. However, the CL which was obtained is way too high in region of 3.7 for AoA of 4!

(selected results from force report)
Force vector: (0.06976 0.997564 0)
pressure total pressure total
force force coefficient coefficient
n n
-------------- --------------
2.2806709 2.2830547 3.7235443 3.7274363
-------------- -------------- -------------- --------------
2.2806709 2.2830547 3.7235443 3.7274363

Could anyone help verify if the parameters used are suitable and correct?

Fluent
(grid checks and scaling have been carried out correctly)
Solver: Pressure-based
Materials: constant density and viscosity
Viscous Model: Spalart-Allmaras (at default values)
Operating Conditions: Op pressure = 101325 Pa
Boundary Conditions: (kindly refer to attached file)
Inlet-velocity inlet
Outlet-pressure outlet

Kindly point out any possible loopholes which i might have in the meshing as well. (FYI airfoil used is GEMINI, c=0.171m, b=1.2)

Thanks in advance!
Attached Images
File Type: jpg Gambit mesh.jpg (100.6 KB, 31 views)
Shaoming is offline   Reply With Quote

Old   April 11, 2019, 00:56
Default
  #2
New Member
 
veerappan
Join Date: Apr 2019
Posts: 15
Rep Power: 7
veera is on a distinguished road
that first force vector is x component ?
x=sin alpha?
veera is offline   Reply With Quote

Old   April 11, 2019, 01:20
Default 3d wing
  #3
New Member
 
veerappan
Join Date: Apr 2019
Posts: 15
Rep Power: 7
veera is on a distinguished road
dear seniors
actually i am simulating naca4412 3d airfoil wing for downloaded conference paper , in that paper i got results , but my solution is very low in the two order deviated from his values
for example . paper result is at 0 AOA , cl=0.0018, cd =-0.05
but my result is cl=0.0016, cd =0.00016
similarly at 5 AOA , PAPER RESULT IS CL=0.2 , CD = 0.1
but my result again cl= 0.0023 , cd = 0.0003
what any thing wrong in inlet parameters what i gave , or in scaling factor , waiting for your response
veera is offline   Reply With Quote

Reply

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


Similar Threads
Thread Thread Starter Forum Replies Last Post
3D Wing Analysis Ed FLUENT 5 April 13, 2019 13:07
multi wing element - negative coefficient of drag? Zweeper FLUENT 10 March 11, 2010 12:20
Problems with repeating results Lee Siemens 4 May 26, 2006 03:39
problems viewing results with VNC Ralf Schmidt FLUENT 3 February 1, 2006 01:40
Boundary layer on a wing Mark FLUENT 0 August 18, 2004 20:24


All times are GMT -4. The time now is 04:03.