NACA 6412 airfoil — dimension sheet Source: Xem Studio, https://xemstudio.com/objects/naca-6412-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 11.97 - NACA 6412 is a 4-digit section with 6% camber at 40% chord and 12% thickness (designation per NASA TM-4741), the most cambered of the common 4-digit 12% family. - Following the 2412 -> 4412 trend in NACA data (zero-lift angle -2 -> -4 deg), more camber gives more lift at a given angle and more nose-down moment (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 6412: 6 % 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: 6% at 40% chord / 12% (NASA TM-4741) - Camber trend (2412 -> 4412): zero-lift angle -2 -> -4 deg (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 0.721 2.188 1.779 -1.450 2.5 1.792 3.244 3.208 -1.790 5 4.097 4.844 5.903 -2.032 7.5 6.505 6.119 8.495 -2.041 10 8.972 7.194 11.028 -1.944 15 14.015 8.910 15.985 -1.597 20 19.149 10.174 20.851 -1.174 25 24.336 11.060 25.664 -0.747 30 29.551 11.609 30.449 -0.359 40 40.000 11.800 40.000 0.200 50 50.176 11.117 49.824 0.550 60 60.302 9.870 59.698 0.796 70 70.362 8.116 69.638 0.884 80 80.340 5.882 79.660 0.784 90 90.224 3.180 89.776 0.487 95 95.127 1.651 94.873 0.266 100 100.000 -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 - 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 - 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 - 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-6412-airfoil/index.json API: https://xemstudio.com/api/geometry?object=naca-6412-airfoil