NACA 4412 airfoil — dimension sheet Source: Xem Studio, https://xemstudio.com/objects/naca-4412-airfoil/ (sheet CC BY 4.0; files Xem Studio Design License, https://xemstudio.com/license/) Basis: Computed from the NACA equations (Report 460 / Report 610, restated in NASA TM-4741) Catalog version: 2026-10-20 Overall (mm): length 100.0, width 20.0, height 11.99 - 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) 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 Files elsewhere (not hosted by Xem Studio; license as stated by the publisher): - 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 — https://ntrs.nasa.gov/citations/19930091108 - NASA: TM-4741: Computer program to obtain ordinates for NACA airfoils (Ladson, Brooks, Hill, Sproles, 1996) — web — Publisher's page; dimensions are facts — https://www.pdas.com/refs/tm4741.pdf - Virginia Tech Pressbooks (data from Abbott & von Doenhoff, NACA): Appendix A: Airfoil Data — web — Publisher's page; dimensions are facts — https://pressbooks.lib.vt.edu/aerodynamics/?p=52 - NASA Langley (Ladson et al.), NASA TM-4741: Computer Program to Obtain Ordinates for NACA Airfoils — web — Publisher's page; dimensions are facts — https://www.pdas.com/refs/tm4741.pdf - Aerospaceweb.org: NACA Airfoil Series — web — Publisher's page; dimensions are facts — https://aerospaceweb.org/question/airfoils/q0041.shtml Free files (Xem Studio Design License, Xem Studio; STEP + STL, 1 parts): https://xemstudio.com/files/hardware/naca-4412-airfoil/index.json API: https://xemstudio.com/api/geometry?object=naca-4412-airfoil