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Lift and Drag on airplane wing

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Old   October 5, 2006, 07:42
Default Lift and Drag on airplane wing
  #1
Arj
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Hi all,

I am trying to run a simulation on wing designs to work out lift and drag coefficients. I am completely new to ANSYS CFX and Ive imported a wing geometry from solidworks to ANSYS. I am unsure how to go about this. I have made a containing box around my 3D model, what do i do from here, I tried to emulate flow around the wing by copying some parameters from the "flow around the blunt body" tutorial. All i have is some pretty colors around my wing. How can i measure velocities, pressures etc at specific sections of my wing. How do i determine lift and drag (forces?)using CFX and change angles of attack? Any help would be appreciated!

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Old   October 5, 2006, 08:36
Default Re: Lift and Drag on airplane wing
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Joe
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You're on the right track. Just do all the tutorials and you will be able able to answer virtually all the questions you have posed, yourself.

Until you have a basic understanding of how CFX works any explanations by others wont really sink in.
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Old   October 5, 2006, 12:09
Default Re: Lift and Drag on airplane wing
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Arj
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cheers for the response! I understand that doing the tutorials is best, and I am endeavouring to do them in the limited time I have. However if possible, I would like a couple of small questions to be answered..Does ANSYS provide features(functions?) to work out lift and drag? Or do I need to manipulate the solved data, and use forces etc. Also how do I incorporate different angles of attack - Do I need to set my fluid flow from a different direction/angle?
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Old   October 5, 2006, 13:35
Default Re: Lift and Drag on airplane wing
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Phil
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Does ANSYS provide features(functions?) to work out lift and drag?

It provides the XYZ components of force which you can then convert to Cl, Cd etc.

Also how do I incorporate different angles of attack

Change the fluid flow angle or the wing angle. Arrange your fluid BCs accordingly.

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Old   October 6, 2006, 04:05
Default Re: Lift and Drag on airplane wing
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Michael B
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For a start look at the overview at the end of the solver run.
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