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March 24, 2007, 09:18
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analyzing NACA 0012 airfoil
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Guest
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Hi everybody! i would like to analyze the NACA 0012 airfoil to determine the lift and drag coefficients at different angle of attack by using cfx. can you please tell me the steps required to achieve that.
thanks M.Hammam. |
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May 2, 2007, 05:19
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Re: analyzing NACA 0012 airfoil
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#2 |
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Guest
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Hello I am an aerospace engeneering and want to NACA 0012 airfoil codes to determine the pressure,lift and drag coefficients at different angle of attack by using cfx. thanks N.Tohidi
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May 3, 2007, 12:07
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Re: analyzing NACA 0012 airfoil
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#3 |
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What do you mean with "codes" ??
The (x,y) coordinates that define the contour of the airfoil? Santiago. |
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May 3, 2007, 12:17
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Re: analyzing NACA 0012 airfoil
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#4 |
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This is really breaking news.
Good luck, Gert-Jan |
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May 7, 2007, 04:47
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Re: analyzing NACA 0012 airfoil
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#5 |
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Guest
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Choose "The Applet" on http://www.mh-aerotools.de/airfoils/javafoil.htm to run JAVAFOIL. Why bother with CFD...
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May 14, 2007, 10:30
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Re: analyzing NACA 0012 airfoil
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#6 |
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Guest
Posts: n/a
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Hello I require analyzing NACA 0012 airfoil. Thanks
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