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Old   January 19, 2008, 21:33
Default Airfoil Coordinates
  #1
Usman
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Hi Guys

How can i find the coordinates of an airfoil at different angle of attacks. I want to simulate a flow over a NACA 0018 airfoil but i have coordinates for it only at 0 degree angle of attack. I need to get its coordinates @ 3, 9 and 12 degrees angles of attack? Thanks in advance

Regards Usman
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Old   January 19, 2008, 22:03
Default Re: Airfoil Coordinates
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ag
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Rotate the airfoil. The transformation can be found in any number of references. Or rotate the freestream flow vector.
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Old   January 19, 2008, 22:19
Default Re: Airfoil Coordinates
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Usman
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Can you explain in a bit more detail how can i rotate the airfoil. What do you mean by number of refernce? I will not be able to use freestream flow vector in my case! Thanks

Usman
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Old   January 20, 2008, 06:27
Default Re: Airfoil Coordinates
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A.K.
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In order to rotate each given point of your airfoil, use simple formulae available, e.g., at http://en.wikipedia.org/wiki/Rotation_(mathematics)
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Old   January 20, 2008, 06:37
Default Re: Airfoil Coordinates
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Usman
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Thanks AK i will look into it!

Usman
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Old   January 23, 2008, 16:41
Default Re: Airfoil Coordinates
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Usman
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Which formulas exactly are we suposse to use to find the co-ordinates for airfoil at an angle of incidence. I am very confused here.

Usman
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Old   January 24, 2008, 07:43
Default Re: Airfoil Coordinates
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A.K.
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Let (x,y) be the frame of reference in which the inflow velocity is (U,0), and (x',y') be coordinates of an airfoil point.

Now if you rotate the point (x',y') with respect to (x,y) clockwise at an angle "alpha" then

x= x'cos(alpha)+y'sin(alpha);

y= -x'sin(alpha)+y'cos(alpha)

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Old   January 24, 2008, 07:53
Default Re: Airfoil Coordinates
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Usman
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Thank you very much AK.

Regards Usman
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