NACA profile coordinates
Hi, anyone know where to get a correct NACA 0012 coordinates? i have generate the coordinates by using JavaFoil software but when i run the simulation by using cosmofloworks i cannot get the same result (lift and drag coefficient against AOA) as the software provided....pls help...thanks..
The best option would be to write your own code. For symmetric NACA 4-series airfoils it's pretty straightforward. See the Wikipedia article below for the equations.
Or you could always visit the UIUC airfoil database. There are tons of airfoil coordinates available.
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