NACA 0015 airfoil — dimension sheet Source: Xem Studio, https://xemstudio.com/objects/naca-0015-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 15.0 - NACA 0015 is a 15% thick symmetric 4-digit section (NASA TM-4741 designation). Like all symmetric sections it has zero lift at zero angle and zero moment about the a.c. (Virginia Tech Appendix A). - Thicker sections give a deeper spar and gentler stall; NACA data on the 2415 vs 2412 show thickening from 12% to 15% slightly increases drag and slightly lowers CLmax (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 0015: symmetric, 15 % 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: 15% 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) - Effect of 12% -> 15% thickness (2412 vs 2415): drag slightly up, CLmax slightly down (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 2.367 1.250 -2.367 2.5 2.500 3.268 2.500 -3.268 5 5.000 4.443 5.000 -4.443 7.5 7.500 5.250 7.500 -5.250 10 10.000 5.853 10.000 -5.853 15 15.000 6.681 15.000 -6.681 20 20.000 7.172 20.000 -7.172 25 25.000 7.426 25.000 -7.426 30 30.000 7.501 30.000 -7.501 40 40.000 7.250 40.000 -7.250 50 50.000 6.608 50.000 -6.608 60 60.000 5.684 60.000 -5.684 70 70.000 4.542 70.000 -4.542 80 80.000 3.214 80.000 -3.214 90 90.000 1.706 90.000 -1.706 95 95.000 0.880 95.000 -0.880 100 100.000 -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-0015-airfoil/index.json API: https://xemstudio.com/api/geometry?object=naca-0015-airfoil