Coord. Request

[coosbaylumber]

Coord. Request

My copy of Compufoil does not recognise some numbers, but could someone run me a set of coordinates for the airfoils labeled as:

NACA 66-010
and for
NACA 66-210.4

These are older model pylon airfoils. Just leave shoot me a P.M. if you can and leave then in a DAT or .COR format. I can handle from there.

Wm.

[kcaldwel]

Attached as txt file, just change to .dat. Not sure about the 210.4 either...Kevin

[MarkusN]

OK, here's the cambered version. Correct designation in NACA nomenclature is: NACA 66(210)-(2)(10.4), i.e. a foil that is derived from the thickness distribution of the NACA 66-210, has a design lift coefficient of 0.2 and a thickness of 10.4% HTH.

BTW, which version of Compufoil do you have? Compufoil PRO is supposed to be able to generate these sections, for any thickness and lift coefficient you specify.

[coosbaylumber]

I will put into a format that Compufoil 1.23 will understand. The first one looks good, it is the second (last) one which looks to be some work.

My version will handle lottsa numbers beyond the decimal point, but that really does little good, for with a 10 inch chord wing, that accuracy is near useless then.

Oh, this same thing was posted at another forum, and had several nasty comments as to the need of it, plus Boo on Compufoil, Boo on ..... All having little to do with generating an airfoil.



Wm.

[CompuFoil]

CompuFoil v1.23 was one of the first Windows version of CompuFoil written for Windows 3.1 and is almost 13 years old. One thing that the old version does not handle the same as the current version of CompuFoil3D are NACA airfoils where the computational zero-zero point is different than the actual nose of the airfoil. Normally these two points are the same, but the NACA airfoil equations produce this kind of anomaly at the leading edge when they are cambered.
Graphically, this shows up as an slightly elevated nose off of the horizantal chord line.
Regards,
Eric Sanders