# NACA 4412 airfoil > What is the exact shape of the NACA 4412 airfoil, and what do the digits mean? - Category: Airfoils › NACA 4-digit - Kind: Standard part - Basis: Computed from the NACA equations (Report 460 / Report 610, restated in NASA TM-4741) - Page: https://xemstudio.com/objects/naca-4412-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=naca-4412-airfoil · Plain text: https://xemstudio.com/objects/naca-4412-airfoil/sheet.txt - License: dimension sheet CC BY 4.0 (Xem Studio); files Xem Studio Design License (free to use and sell from, not to redistribute as files: https://xemstudio.com/license/) - Use in every chat: add https://xemstudio.com/mcp as a connector (https://xemstudio.com/use-with-ai/) ## Overall (mm) | length | width | height | |---|---|---| | 100.0 | 20.0 | 11.99 | **Exact dimensions.** True size, with no printing tolerance added. ## 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) ## Sizes | 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 - 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)](https://ntrs.nasa.gov/citations/19930091108) — web — Publisher's page; dimensions are facts - NASA: [TM-4741: Computer program to obtain ordinates for NACA airfoils (Ladson, Brooks, Hill, Sproles, 1996)](https://www.pdas.com/refs/tm4741.pdf) — web — Publisher's page; dimensions are facts - Virginia Tech Pressbooks (data from Abbott & von Doenhoff, NACA): [Appendix A: Airfoil Data](https://pressbooks.lib.vt.edu/aerodynamics/?p=52) — web — Publisher's page; dimensions are facts - NASA Langley (Ladson et al.), NASA TM-4741: [Computer Program to Obtain Ordinates for NACA Airfoils](https://www.pdas.com/refs/tm4741.pdf) — web — Publisher's page; dimensions are facts - Aerospaceweb.org: [NACA Airfoil Series](https://aerospaceweb.org/question/airfoils/q0041.shtml) — web — Publisher's page; dimensions are facts ## Free STEP/STL (1 parts, Xem Studio Design License, Xem Studio) Index: https://xemstudio.com/files/hardware/naca-4412-airfoil/index.json · license: https://xemstudio.com/files/hardware/naca-4412-airfoil/LICENSE.md - naca-4412-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/naca-4412-airfoil/naca-4412-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/naca-4412-airfoil/naca-4412-airfoil-section-100mm-chord.stl) — NACA 4412 section, 100 mm chord × 20 mm span, closed trailing edge, 160 points from the equations (scale to your chord) ## 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. ## Fits with - [NACA 4409 airfoil](https://xemstudio.com/objects/naca-4409-airfoil/) - [NACA 4415 airfoil](https://xemstudio.com/objects/naca-4415-airfoil/) - [NACA 4418 airfoil](https://xemstudio.com/objects/naca-4418-airfoil/) - [NACA 4421 airfoil](https://xemstudio.com/objects/naca-4421-airfoil/) - [NACA 4424 airfoil](https://xemstudio.com/objects/naca-4424-airfoil/)