NACA 2412 airfoil — dimension sheet Source: Xem Studio, https://xemstudio.com/objects/naca-2412-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 12.0 - NACA 2412 has 2% camber at 40% chord and 12% thickness (designation per NASA TM-4741). NACA data give CL of about 0.25 at zero angle, a zero-lift angle of -2 deg and CLmax about 1.7, up from about 1.6 for the 0012 (Virginia Tech Appendix A). - Its quarter-chord moment is roughly constant and negative (nose-down) between stall onsets (Virginia Tech). - 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 2412: 2 % 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: 2% at 40% chord / 12% (NASA TM-4741) - CL at 0 deg: about 0.25 (Virginia Tech Appendix A) - Zero-lift angle: -2 deg (Virginia Tech Appendix A) - CLmax (Re 6e6): about 1.7 (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 1.067 2.008 1.433 -1.762 2.5 2.256 2.845 2.744 -2.361 5 4.690 4.010 5.310 -3.072 7.5 7.160 4.866 7.840 -3.506 10 9.650 5.545 10.350 -3.795 15 14.667 6.553 15.333 -4.116 20 19.713 7.230 20.287 -4.230 25 24.777 7.655 25.223 -4.218 30 29.850 7.874 30.150 -4.124 40 40.000 7.800 40.000 -3.800 50 50.059 7.230 49.941 -3.341 60 60.101 6.324 59.899 -2.768 70 70.121 5.132 69.879 -2.132 80 80.114 3.680 79.886 -1.458 90 90.076 1.974 89.924 -0.752 95 95.043 1.022 94.957 -0.383 100 100.000 -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 - engrXiv (Bhattacharya et al., ICMMM 2023): Design and Computational Analysis of Y-tail Configuration for Maritime UAV — web — Publisher's page; dimensions are facts — https://engrxiv.org/preprint/download/6582/10812/9153 Free files (Xem Studio Design License, Xem Studio; STEP + STL, 1 parts): https://xemstudio.com/files/hardware/naca-2412-airfoil/index.json API: https://xemstudio.com/api/geometry?object=naca-2412-airfoil