# Simulation of a complex wing in solidworks flow simulation

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 February 23, 2011, 07:07 Simulation of a complex wing in solidworks flow simulation #1 New Member   Niels Join Date: Feb 2011 Posts: 4 Rep Power: 7 Hi all, Im trying to simulate an aircraft wing in flow simulation and retreive information such as the lift coefficient and the drag coefficient of the total wing. So i started to do a tutorial of an airflow over a wing in a 2D situation described in (http://books.google.com/books?id=w_T...page&q&f=false) Chapter 4. When i followed the tutorial i get quite the same results as the tutorial. Then i tried to simulate a Clark V profile with exactly the same settings, even the same model size. But the results are not satisfying. The lift coefficient we calculate from the given Y-force is about 0.057, but it must be about 0.2259 according to the Cl/alfa table. Here im working with the same reynoldsnumber. I also tried other wing profiles and played with some settings of the simulation but i dont get any realistic results. I think the turbulence intensity and the turbulence lenght are an important factor, but I dont know what the exact meaning is of these variables and how to determine their correct values. So im stuck at a relative simple 2D simulation of a wing, and i also want to do a 3D simualtion (in air and also in water) which I think is more complex to perform. Can anyone help me and tell me what im doing wrong? And is the flow simulation option in solidworks accurate enough to determine the lift and drag of a wing? I want to use the values for a school project, so it must be quite accurate.

 March 1, 2011, 05:44 #2 New Member   Niels Join Date: Feb 2011 Posts: 4 Rep Power: 7 Really nobody with some suggestions?

 April 5, 2011, 13:10 #3 New Member   Kooky Join Date: Mar 2011 Location: Thailand Posts: 20 Rep Power: 7 I think the geometry is effect with the results. You should be create the geometry by reference from origin. Can you show your model picture?

 April 7, 2011, 05:59 Pictures #4 New Member   Niels Join Date: Feb 2011 Posts: 4 Rep Power: 7 Hi, I do not really understand your comment, but here are some pics anyway To draw the profile i used curve through points (imported from profili). I had to split it into two curves because otherwise the function made the trailing edge a round edge, to split it up into two at the trailing edge it becomes a sharp edge. Btw, i also made a model where a large plate on the YX front plane is attached to the wing. but then the wing visually shows a very bad curve, the upper part is made up of 1 line from half of the chord to the trailing edge. Is this pure a visual problem in solidworks, or does it physicly changes my object? Thanks for responding btw!

 April 7, 2011, 10:30 #5 New Member   Kooky Join Date: Mar 2011 Location: Thailand Posts: 20 Rep Power: 7 The geometry is important to obtain the result accuracy. The picture below shows different coordinate. The center of mass of the first case is started at the origin but offset from the origin for the second case. The boundary conditions of both cases were same condition. So, the results are different. Center of mass at origin.jpg offset center of mass from origin.jpg Turbulent intensity is the ratio of the root mean square of the velocity fluctuations to the mean flow velocity. In your case, the low turbulence intensity should be apply on it. Good luck

April 9, 2011, 09:30
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Quote:
 Originally Posted by niels1900 I want to use the values for a school project, so it must be quite accurate.

This kind of problem is fairly theoretical and I think its known that general purpose solvers fair less than optimally for these kinds of problems such as 2d cross sections of airfoils for lift and drag.

 April 20, 2011, 10:44 #7 New Member   Alain FRYDMAN Join Date: Mar 2009 Posts: 8 Rep Power: 9 IMO Your discrepancy between the simulation and theorical results are just too large to be explained by turbulence farfiel values. You should check that you use the correct coordinate system. Moreover, as you made a 2D calculation your actual domain thickness is usually far more smaller than the modelled geometry. So even if you modelled a 1 m thick airfoil the integration made by flowsimulation can be made on a smaller lenght that would explain why your lift force is so small.

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