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NACA 4412 airfoil
What is the exact shape of the NACA 4412 airfoil, and what do the digits mean? · Standard part · basis: Computed from the NACA equations (Report 460 / Report 610, restated in NASA TM-4741)
Also called: NACA 4412, NACA 4412 coordinates, NACA 4412 dat, NACA 4412 profile, NACA 4412 DXF, NACA 4412 STEP, NACA 4412 STL, perfil NACA 4412, Profil NACA 4412, naca4412, NACA 4412 wing section
Exact dimensions. True size, with no printing tolerance added.
- length
- 100.0 mm
- width
- 20.0 mm
- height
- 11.99 mm
Notes
- NACA 4412 doubles the 2412's camber to 4% at 40% chord with 12% thickness (NASA TM-4741). The zero-lift angle drops to -4 deg and lift at zero angle rises relative to the 2412 (Virginia Tech Appendix A).
- Its quarter-chord moment is negative (nose-down) and roughly constant between stall onsets, so more camber means more trim load on the tail (Virginia Tech Appendix A).
- NACA 4-digit sections have good stall behaviour, small centre-of-pressure movement and low roughness sensitivity, but a low CLmax, relatively high drag and high pitching moment (Aerospaceweb summary).
- NACA 4412: 4 % camber at 40 % chord, 12 % thick.
- NACA 4-digit: first digit = maximum camber in % of chord, second = its position in tenths of chord, last two = maximum thickness in % of chord (NACA Report 460).
- Ordinates are in % of chord from the leading edge, computed from the published equations with the closed-trailing-edge thickness coefficient (−0.1036, as in NASA TM-4741). The original reports use an open trailing edge (−0.1015); the difference is under 0.03 % of chord near the trailing edge.
- The file is a 100 mm chord section, 20 mm deep: scale it uniformly to your chord, or import the STEP and sweep or loft it into a wing. Thickness scales with chord; the shape is the same at any size.
- Max camber / position / thickness: 4% at 40% chord / 12% (NASA TM-4741)
- Zero-lift angle: -4 deg (Virginia Tech Appendix A)
- Cm c/4: negative, roughly constant (Virginia Tech Appendix A)
- 4-digit code: 1st digit max camber %c; 2nd digit camber position in tenths c; last two thickness %c (NASA TM-4741; Aerospaceweb)
- Thickness equation (t/c = 0.20 basis): y/c = 0.2969 sqrt(x) - 0.1260 x - 0.3516 x^2 + 0.2843 x^3 - 0.1015 x^4, scaled by (t/c)/0.20 (NASA TM-4741)
NACA 4412 airfoil size chart
| x (% chord) | upper x | upper y | lower x | lower y |
|---|---|---|---|---|
| 0 | 0.000 | 0.000 | 0.000 | 0.000 |
| 1.25 | 0.890 | 2.105 | 1.610 | -1.613 |
| 2.5 | 2.018 | 3.054 | 2.982 | -2.086 |
| 5 | 4.387 | 4.439 | 5.613 | -2.564 |
| 7.5 | 6.826 | 5.505 | 8.174 | -2.786 |
| 10 | 9.305 | 6.381 | 10.695 | -2.881 |
| 15 | 14.337 | 7.741 | 15.663 | -2.866 |
| 20 | 19.429 | 8.709 | 20.571 | -2.709 |
| 25 | 24.556 | 9.362 | 25.444 | -2.487 |
| 30 | 29.700 | 9.743 | 30.300 | -2.243 |
| 40 | 40.000 | 9.800 | 40.000 | -1.800 |
| 50 | 50.117 | 9.174 | 49.883 | -1.396 |
| 60 | 60.202 | 8.098 | 59.798 | -0.987 |
| 70 | 70.242 | 6.626 | 69.758 | -0.626 |
| 80 | 80.228 | 4.784 | 79.772 | -0.339 |
| 90 | 90.151 | 2.579 | 89.849 | -0.134 |
| 95 | 95.085 | 1.338 | 94.915 | -0.060 |
| 100 | 100.000 | -0.000 | 100.000 | 0.000 |
Where the files are
Other publishers' files are linked, not hosted. "verify" = check the license at the link before commercial use.
| NACA (NASA Technical Reports Server) | Report 460: The characteristics of 78 related airfoil sections from tests in the variable-density wind tunnel (Jacobs, Ward, Pinkerton, 1933) | web | Publisher's page; dimensions are facts |
| NASA | TM-4741: Computer program to obtain ordinates for NACA airfoils (Ladson, Brooks, Hill, Sproles, 1996) | web | Publisher's page; dimensions are facts |
| Virginia Tech Pressbooks (data from Abbott & von Doenhoff, NACA) | Appendix A: Airfoil Data | web | Publisher's page; dimensions are facts |
| NASA Langley (Ladson et al.), NASA TM-4741 | Computer Program to Obtain Ordinates for NACA Airfoils | web | Publisher's page; dimensions are facts |
| Aerospaceweb.org | NACA Airfoil Series | web | Publisher's page; dimensions are facts |
Free files
★ Free files 1 parts. Xem Studio design: free to use, print and sell things from; not to be republished as files. Xem Studio Design License. index.json
| naca-4412-airfoil-section-100mm-chord | NACA 4412 section, 100 mm chord × 20 mm span, closed trailing edge, 160 points from the equations (scale to your chord) | STEP · STL |
https://xemstudio.com/mcp to Claude, ChatGPT, Cursor or any MCP client (free, no account, one minute) and it can look up exact sizes, mating fits and free STEP/STL from every chat.Plain text: sheet.txt · JSON: /api/geometry?object=naca-4412-airfoil
Fits with
Questions
2412 or 4412?
4412 has twice the camber: zero-lift angle -4 deg vs -2 deg, more lift at a given angle, more nose-down moment (Virginia Tech).
How thick is the NACA 4412?
Maximum thickness 11.99 % of chord at 30.3 % chord: 11.99 mm on a 100 mm chord.
Where is the NACA 4412's camber?
Maximum camber 4.00 % of chord at 40.0 % chord.
How do I use it for my wing?
Scale the 100 mm section to your chord (e.g. 180 mm chord = 180 % scale), then extrude or loft between root and tip sections. For a tapered wing, scale a root and a tip copy and loft between them.