Question about meshing 2D airfoil in icemcfd
 

I am doing the meshing for 2D airfoil naca0012 in icem cfd, the grid came out is not nice in the leading edge because of the lack of formatted point data at the frontal part.I want to build the data using C++,I know the equation,but I dunno how to make the steps for variable-X,the data found from internet is
something like
1.00000 0.00126 0
0.99280 0.00227 0
0.97989 0.00405 0
0.96352 0.00627 0
0.94455 0.00878 0
0.92350 0.01151 0
0.90075 0.01438 0
0.87658 0.01735 0
......
I want to make more precise point,do anyone know how to solve this?
Thanks.

Javafoil
 

You can obtain a number of point for a lot of profile that you want downloading JavaFoil at http://darwin.wcupa.edu/webapps/javafoil/
good luck.

Thank you!