Uploaded August 2016 | Updated September 2026, 2 weeks ago
In this video I'll take you through my step-by-step procedure for 3D printing an airfoil.
We start with the creation of a coordinate file in MATLAB, which is essentially just a list of X and Y data points that describe the shape of the airfoil. Then we load the resulting Excel file into Inventor, and make the model that we want to print. Then we export the model as an STL file and load it into Slic3r, where we get the printing orientation correct, along with the actual printing instructions/settings. Finally, we print the airfoil!
NOTE 1 (Time = 0:30)
For this particular print, because it was so small, the trailing edge ended up being just a single line thick (one pass from the extrusion nozzle). This means it wouldn't have mattered if I had left this as 'closed'. For big enough airfoils, you will be able to notice a difference.
NOTE 2 (Time = 7:01)
I leave the infill as 20% here, but because the airfoil was so small to begin with, it just filled it in solid, as you can see when I go to the Layers tab at around 7:40 and scroll through the layers.
NOTE 3 (Time = 15:50)
I get a little jittery when I see that the plastic isn't sticking immediately, so I slowed it down. It might have been fine without me slowing it down. There's a chance that I would have gotten a better bottom edge on my airfoil (as you'll see me complain about after the print is finished). You'll also see me messing with the speed throughout the sped-up video in a second. I'm going to stop interfering with these prints in the future, as it might be making things worse.
In this video I'll take you through my step-by-step procedure for 3D printing an airfoil.
We start with the creation of a coordinate file in MATLAB, which is essentially just a list of X and Y data points that describe the shape of the airfoil. Then we load the resulting Excel file into Inventor, and make the model that we want to print. Then we export the model as an STL file and load it into Slic3r, where we get the printing orientation correct, along with the actual printing instructions/settings. Finally, we print the airfoil!
NOTE 1 (Time = 0:30)
For this particular print, because it was so small, the trailing edge ended up being just a single line thick (one pass from the extrusion nozzle). This means it wouldn't have mattered if I had left this as 'closed'. For big enough airfoils, you will be able to notice a difference.
NOTE 2 (Time = 7:01)
I leave the infill as 20% here, but because the airfoil was so small to begin with, it just filled it in solid, as you can see when I go to the Layers tab at around 7:40 and scroll through the layers.
NOTE 3 (Time = 15:50)
I get a little jittery when I see that the plastic isn't sticking immediately, so I slowed it down. It might have been fine without me slowing it down. There's a chance that I would have gotten a better bottom edge on my airfoil (as you'll see me complain about after the print is finished). You'll also see me messing with the speed throughout the sped-up video in a second. I'm going to stop interfering with these prints in the future, as it might be making things worse.
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The angle of attack (AoA) is one of the most important parameters when studying how planes fly. By definition, it is the angle between some reference line of the plane (in our case the chord line of the wing) and the relative wind. The AoA will be vital when talking about lift curves and how wings generate lift.
Chord Line: http://www.youtube.com/watch?v=Eh5W61iswSY Explained: Angle of Attack [Airplanes]](https://i.ytimg.com/vi/Fm2Az-PgPUU/mqdefault.jpg)




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Want to look at a picture of a bullet/plane/etc. and be able to approximate the Mach number? In the previous video on this topic (linked to below), I showed three different methods of approximating the Mach number from angles measured in a Schlieren image.
https://goo.gl/50saau
When using the Taylor-Maccoll code, I used the shock wave angle and the Mach number guess as inputs to return a cone angle. The cone angle was then compared to the cone angle measured in GIMP using the Measure Tool. In this video, Ive updated the code so that it plots a contour plot of the Mach number (cone plotted in black). I am able to overlay that image onto the actual Schlieren image, adjust the opacity of the overlay, and compare the solution from Taylor-Maccoll theory to the actual shock seen in testing.
Photo Credit:
By NASA Glenn Research Center [Public domain], via Wikimedia Commons How To: Find Mach Number from a Picture (Part 2)](https://i.ytimg.com/vi/H25svaGf9-Y/mqdefault.jpg)

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Its extremely important to understand the assumptions used to derive an equation. This video goes over the assumptions we will be using for the Taylor-Maccoll conical flow problem, and the impact each assumption will have later on in the derivation. Explained: Assumptions for Axisymmetric Conical Flow [Taylor-Maccoll]](https://i.ytimg.com/vi/HIDeIZO0z-8/mqdefault.jpg)

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At transonic speeds, shocks waves form on the wings of an aircraft. Wave drag due to the presence of shocks can become a large portion of the overall drag on the aircraft. A supercritical airfoil can be used to delay the onset of shocks, and thus enable faster cruising speeds.
If you would like some more background on the subject, feel free to watch the following videos.
http://goo.gl/hCKHgf
http://goo.gl/iFxmXs
There are a couple things I want to mention briefly regarding drag. I mentioned the critical Mach number in the video, but neglected to include the drag divergence Mach number. Nothing particularly special happens at the critical Mach number. The shock wave or pressure wave that is formed is actually fairly weak because the flow doesn’t need to slow down too much through the shock wave. There is, however, a freestream Mach number at which the drag starts to suddenly increase quite a bit. This Mach number is the drag divergence Mach number, and is actually more important than the critical Mach number when designing planes. Wave drag occurs due to the presence of shock waves, and as the Mach number increases, wave drag also increases. If you’d like to read some more about the drag divergence Mach number, here are some references to get you started.
Modern Compressible Flow, John D. Anderson, pg. 345
http://en.wikipedia.org/wiki/Drag_divergence_Mach_number
http://www.adl.gatech.edu/research/extrovert/classes/hispd/hispd_notes06.pdf
http://adg.stanford.edu/aa241/drag/cdcintro.html
http://naca.central.cranfield.ac.uk/reports/1947/naca-tn-1396.pdf (pg. 6 under Drag Characteristics) Explained: Supercritical Airfoil [Airplanes]](https://i.ytimg.com/vi/HfW5YTjnp8k/mqdefault.jpg)