Explained: NACA 4-Digit GUI Part 10/10 [MATLAB]

This is the last video in my 10-video series on coding a program in MATLAB to compute, display, and save a NACA 4-digit airfoil.

IN THIS VIDEO:

We add in the code for saving the airfoil data out to a text file. Both the LE to TE and TE to LE methods are coded. A comparison between the output from this code and the data from the UIUC airfoil data site (see link below) is made to confirm that our code works the way it should.

UIUC Airfoil Data Site:

IN THIS SERIES:

If you've made it this far, thanks for watching! I hope you enjoyed it. Let me know if you have any questions or comments.

[showright]

Hi Josh, I came across your GUI script today when searching for a fast way to amass a large number of 4-digit NACA aerofoils, and your script is superb. I've tried to add a couple lines of script to make the final .txt file directly readable into my current working program (ICEM CFD), but I haven't had any luck so far. I'm attempting to add a third column of zeros in the .txt file to indicate the 2D of the aerofoil, as well as including the total number of points used and the number of curves (in my case this would just read 1, as I'm studying closed TE). I spent today watching this series as well as your videos on the background theory, but I can't seem to generate the final .txt file described, and was hoping you could point me in the right direction. Would you be able to point out which section in the script I would have to alter? Thanks very much.

[avrupadabiremir]

I have another question. I wanted to upgrade this gui and added chord length and dynamic axis.

Now i want to do two things. First is zooming to plot which it is ok for me i found it on internet. But second thing is scaling the plot of airfoil.
I mean i want to scale up or down the airfoil for a selected point on the plot. Selecting a point is ok, but i couldn't do the scale thing. I tried to change the chord length but when chord length changed thickness is changed or changed so little. I didn't get it.
And when i want to take "yt" values i couldn't see that on workspace and couldn't get it. So how can i do this, any ideas? Thank you.

[yuckluck]

I plot the airfoil geometry but I notice that there is a gap between points at the leading edge. I used the cosine spacing formula 0.5*(1-1cos(beta)) in my non-uniform if statement and I still see the gap at the leading edge. Any tips on alleviating this problem? I am using the airfoil for ANSYS CFX so that gap may be a problem.

[abylkaiyromar]

could you give access to full, atlab code?