Hi,

I'm working on a project about plasma actuators placed on a wing tip. For that, I'm looking for the airfoil data (points) for the NACA4418 profile. I already have these points but these are not enough to model accurately the wing section. Has anyone any idea to know how i can do to have more points ? Thanks !

hellow,Gilles you can get your airfoil data (x,y) coordinates using this link: http://www.pagendarm.de/trapp/progra...les/NACA4.html but i think you have to install java on your computer. have nice, ali

Thanks a lot for your help !

I use the spline fitting in matlab to fit splines to the top and bottom half of the airfoil and then use that to cluster or increase the number of points.

-H

Dear Sir/Madam

I would like to have the NACA 4418 in the text format file

Thanks

I'm university student

so, I like to me send me experomental data for lift

cofficient and monent cofficient about the quarter-chord

point & experimental data for profile drage cofficienst

and moment cofficient about NACA4418, NACA 0008, NACA 0012

Those just use to homework...so if you send me that I will

be appreciation

Thank you

Hello,Karthi and ku ja-kuck, simply,go to:http://www.pagendarm.de/trapp/progra...les/NACA4.html you can obtain your NACA coordinates.copy and past them in a new file.txt (note pade file). have a nice.