Clark y airfoil generation

[guymlink]

I have been trying to figure out how to make a sketch that will be an airfoil for a wing. specifically I need this sketch to allow me to change a few parameters and it would make the wing I want. I either need the parameters to let me enter a 4 digit NACA, or, Preferably, to enter the Chord Length, Max Thickness, and location of max thickness. I have some more complicated questions after that, but they make more since to make another forum post for after this is figured out. anybody have any ideas? my issues have been with making the curves behave reasonably. adding parameters I have figured out I think.

[blandb]

Does the link below help you?

https://www.youtube.com/watch?v=Xo0tqe-frs8

[CCarreiras]

Hi!

You have to do several sections, create the profile with sketches,  and connect them with loft tool.

[guymlink]

almost! and it is certainly usable. it dose not give me nearly the freedom I wish. but had not see the video yet. vary helpful.

[blandb]

There was another option where users can grab specific company type airfoils, but they are in an excel format. Then the user would have to import that into a sketch, but would be just stagnant points. You would have do dimension all points and add all kinds of geometry to find what you were doing. You probably could of sketched it with equation curves by the time you imported and defined everything. Sorry, I don't do airfoils, so I am not too sure of the required inputs a user would need.

[guymlink]

I have done a lot of the importing excel points and using a spline from a generator method. I just want to be able to change it as I go in inventor. the main issue with (his) equation anyways is A, he never posted it and I tried copying from on screen with no success, lol, B it's a symmetrical airfoil. witch is basically all the math you need - the curve of the chord (camber) for a normal airfoil. and I don't know anything about equation curves and cant add that part in.

[blandb]

Did you create the user parameters "chord" and "thick". Maybe that is why yours failed? If those parameters didn't exist, then it would not work.

[guymlink]

I did. I think its just that the resolution is so low and im just copying it incorrectly. ik that this is the equation it is derived from, just cant get it to work in inventor

yt=5tc[0.2969xc−−√+(−0.1260)(xc)+(−0.3516)(xc)2+0.2843(xc)3+(−0.1015)(xc)4

[blandb]

Make sure your thick is unitless "ul" and chord is "in"

x(t) = t^2

y(t) = thick*chord*t*5*(.2969*sqrt(1in/chord)-(.1260*t*1 in)/chord-(.3516*t^3*1 in^2)/chord^2 +(.2843*t^5*1 in^3)/(chord^3)-(.1015*t^7*1 in^4)/(chord^4))

tmin = 0

tmax = sqrt(chord / 1 in)