NACA 0012 airfoil — dimension sheet Source: Xem Studio, https://xemstudio.com/objects/naca-0012-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 0012 is the classic 12% symmetric section. NACA data show zero lift at zero angle and a quarter-chord moment essentially zero from -12 to +14 deg, confirming c.p. and a.c. coincide (Virginia Tech Appendix A). - CLmax at Re 6e6 is just under 1.6, rising to 2.4 with a 20% chord plain flap at 40 deg (Virginia Tech, from Abbott & von Doenhoff). - 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 0012: symmetric, 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 thickness: 12% chord (from designation) (NASA TM-4741) - Camber: 0 (symmetric) (NASA TM-4741) - Zero-lift angle: 0 deg (symmetric section) (Virginia Tech Appendix A) - Moment about a.c.: zero (symmetric; c.p. = a.c.) (Virginia Tech Appendix A) - CLmax (Re 6e6, smooth): just under 1.6 (Virginia Tech Appendix A) - CLmax with 20% flap at 40 deg: 2.4 (Virginia Tech Appendix A) - Cm c/4 flat range: about -12 to +14 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 1.250 1.894 1.250 -1.894 2.5 2.500 2.615 2.500 -2.615 5 5.000 3.555 5.000 -3.555 7.5 7.500 4.200 7.500 -4.200 10 10.000 4.683 10.000 -4.683 15 15.000 5.345 15.000 -5.345 20 20.000 5.737 20.000 -5.737 25 25.000 5.941 25.000 -5.941 30 30.000 6.001 30.000 -6.001 40 40.000 5.800 40.000 -5.800 50 50.000 5.286 50.000 -5.286 60 60.000 4.547 60.000 -4.547 70 70.000 3.634 70.000 -3.634 80 80.000 2.572 80.000 -2.572 90 90.000 1.365 90.000 -1.365 95 95.000 0.704 95.000 -0.704 100 100.000 -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-0012-airfoil/index.json API: https://xemstudio.com/api/geometry?object=naca-0012-airfoil