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

Simulating flow past airfoil with different AOA

Register Blogs Community New Posts Updated Threads Search

Reply
 
LinkBack Thread Tools Search this Thread Display Modes
Old   February 26, 2007, 08:58
Default Simulating flow past airfoil with different AOA
  #1
ramin
Guest
 
Posts: n/a
Hi,

I am now trying to simulate unsteady flow past airfoil with different AOA (angle of attack). I've used gambit to generate the structured grids and successfully simulated the flow at 0deg AOA using fluent. Due to the limitation of the software, it is not possible to generate an airfoil with some other AOA.

Hence, I am wondering if it is possible to just change the AOA by changing my initial/boundary conditions ie instead of u=1,v=0 at inlet, u=0.707=v for 45deg AOA.

Will there be problems? Or is generating an airfoil at different AOA a more popular approach? Can someone recommend a suitable structured grid generator to do that?

Thanks alot
  Reply With Quote

Old   February 26, 2007, 15:53
Default Re: Simulating flow past airfoil with different AO
  #2
Sujith
Guest
 
Posts: n/a
For airfoil the boundary condition will be ususally farfield bounday condition. Here you can specify the flow direction according to angle of attack..

There are tutorials available on airfoil simulation at www.studentfluent.com
  Reply With Quote

Old   February 27, 2007, 04:37
Default Re: Simulating flow past airfoil with different AO
  #3
ramin
Guest
 
Posts: n/a
It's better to clarify my question Quarkz asked ""I am now trying to simulate flow past airfoil with different AOA (angle of attack). I've used a software called MeshPilot to generate the structured grids and successfully simulated the flow at 0deg AOA using my FVM NS solver. Due to the limitation of the software, it is not possible to generate an airfoil with some other AOA. Hence, I am wondering if it is possible to just change the AOA by changing my initial/boundary conditions ie instead of u=1,v=0 at inlet, u=0.707=v for 45deg AOA. Will there be problems? Or is generating an airfoil at different AOA a more popular approach? Can someone recommend a suitable structured grid generator to do that?" in Mon, 26 Dec 2005 (subject:Simulating flow past airfoil with different AOA)

and ag answered "Your approach will work fine assuming your freestream is steady. It's referred to as a Galilean transformation. Just remember that lift and drag coefficients are computed parallel and normal to the freestream flow, and are not the components of the force in the x-y coordinate system (except for aoa=0). If you want to change the angle of your airfoil, why not just rotate the grid? It's a simple transformation and is the approach I follow. Write yourself a simple program to apply the transformation.""

Now,I'd like to know if i simulate flow past airfoil with different AOA in incompressible and unsteady case,it's possible to change the AOA by changing my initial/boundary conditions(like example of Quarkz). it's seems from answer ag this approach will work only with steady case.Will there be problems in unsteady case? my inlet BC is velocity inlet and outlet is outflow. Thanks alot
  Reply With Quote

Old   February 27, 2007, 06:20
Default Re: Simulating flow past airfoil with different AO
  #4
HSeldon
Guest
 
Posts: n/a
Hi, question... How did you exported the mesh file generated with meshpilot in order to read it with Fluent and/or Gambit? Regarding your problem, I think that you can change the AOA without problems, because MeshPilot generates a parabolic far-field. Just go to the boundary condition panels and change the versors in the direction field.

  Reply With Quote

Old   April 22, 2015, 14:09
Default
  #5
New Member
 
Anthony McCarthy
Join Date: Nov 2014
Location: United Kingdom
Posts: 21
Rep Power: 11
antm324 is on a distinguished road
Hi Ramin,

from what i understand from your question you are asking if it is possible to change the angle of attack of the airfoil with out rotating the geometry and re-meshing?

If so , yes use your initial conditions of a velocity inlet to enter the components (x, y) velocities of flow for that given angle of attack.
antm324 is offline   Reply With Quote

Reply


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
Flow past 2 smooth circular cylinder slip FLUENT 0 July 8, 2010 19:45
Airfoil conditions for unsteady flow Dave Main CFD Forum 3 April 24, 2008 18:11
Airfoil boundary condition Frank Main CFD Forum 1 April 21, 2008 19:36
simulation of a turbulent flow on airfoil Dante FLUENT 3 June 8, 2007 15:54
Modelling flow over airfoil at near stall angle Kelvin FLUENT 5 June 6, 2007 03:00


All times are GMT -4. The time now is 02:48.