I am working on design of NACA 63415 airfoil for my research.Besides computational methods,I am interested to do the profile mathematically.Can anyone tell me what is the chord length equation for a 6 series NACA airfoils.Thanks
Using this website: http://airfoiltools.com/plotter/index?airfoil=n63415-il
you can set the chord you want and the airfoil coordinates will be generated. If you click "CVS file of coordinates" you can download the coordinates to import them into EXCEL. If you leave the chord as 100, then the coordinates are still given in percent of chord so you can put the the coordinates in EXCEL and then multiply them by any chord to get the correct coordinates for the desired chord. You can also use the curve fit in EXCEL to get an equation for the profile.
See www.HowFliesTheAlbatross.com "parametric geometry" for powerful and contemporary methods of math modeling airfoils. You can use these methods to accurately characterize any airfoil, and then adjust one or more parameters if you are conducting an optimization.