hello dear collegue, i'm going to do a numerical investigation of the effects of geometry parameters on NACA airfoils using cfx. so to creat geometry,i need coordinates (x,y)with cord=100mm. what i have got from "NACA coordinates.dat",that existes in web sites literature, is corresponding to cord=1000m.

My question is:how to comput NACA0010 coordinates(for example) but considering: cord=100mm? thank you.

Just scale the results by the ratio of chord lengths.

Hello!

On web you can find NACA airfoil coordinate generation program. Copy this coordinetes in MS Excel and multiply them by 100. Now you have coordinates for chord 100mm.

a1=1.5 a2=-0.6 a3=-1.7 a4=1.4 a5=-0.5 y=-t*(a1*x^0.5+a2*x+a3*x^2+a4*x^3+a5*x^4)

works for NACA airfoils,where t is the thickness.

I think that it is better to use coordinate generator than this equation. This is just thicknes distribution.

thanks ag,marek and Harish for your usefull suggestions.