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#1 |
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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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#2 |
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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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#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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#4 |
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This is really breaking news.
Good luck, Gert-Jan |
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#5 |
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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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#6 |
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Hello I require analyzing NACA 0012 airfoil. Thanks
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Thread | Thread Starter | Forum | Replies | Last Post |
[Commercial meshers] Naca 0012 airfoil | naveen | OpenFOAM Meshing & Mesh Conversion | 7 | April 14, 2011 11:03 |
problem with stall in naca 0012 airfoil | thanos | FLUENT | 0 | February 18, 2010 11:36 |
Laminar flow past oscillating Naca 0012 airfoil | kafkaf | Main CFD Forum | 1 | April 7, 2009 02:49 |
Solving naca 0012 airfoil | naveen | OpenFOAM Pre-Processing | 3 | February 17, 2009 09:25 |
Drag predicion for a NACA 0012 airfoil | Peter Giannakopoulos | FLUENT | 7 | March 9, 2004 15:32 |