NACA 23015 airfoil — dimension sheet Source: Xem Studio, https://xemstudio.com/objects/naca-23015-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 23015 is the 15% thick member of the 230 family: design CL 0.3, maximum camber at 15% chord (Aerospaceweb; NASA TM-4741). - NACA 5-digit sections offer higher CLmax and low pitching moment with low roughness sensitivity, but poor (abrupt) stall and relatively high drag (Aerospaceweb summary). - Thicker sections suit wing roots where spar depth matters; NACA data on 2412 vs 2415 show the extra thickness slightly raises drag and lowers CLmax (Virginia Tech). - NACA 23015: 5-digit 230 mean line (design lift coefficient 0.3, camber peak at 15 % chord), 15 % thick. - NACA 5-digit 230xx: '2' × 3/2 = design lift coefficient 0.3; '30' = camber peak at 15 % chord on a simple mean line; last two digits = maximum thickness in % of chord (NACA Report 610; TM-4741). - 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. - 5-digit code: 1st digit x 3/2 = design CL in tenths; next two digits / 2 = max camber position in tenths c; last two thickness %c (Aerospaceweb) - 230 camber line: design CL 0.3, max camber at 15% chord (Aerospaceweb; NASA TM-4741 (cl,i = 0.3)) - Thickness: 15% chord (designation) x (% chord) upper x upper y lower x lower y 0 0.000 0.000 0.000 0.000 1.25 0.642 2.644 1.858 -1.931 2.5 1.770 3.852 3.230 -2.520 5 4.283 5.540 5.717 -3.230 7.5 6.938 6.711 8.062 -3.728 10 9.639 7.543 10.361 -4.141 15 15.001 8.520 14.999 -4.843 20 20.158 8.937 19.842 -5.403 25 25.164 9.080 24.836 -5.768 30 30.166 9.045 29.834 -5.953 40 40.160 8.573 39.840 -5.923 50 50.146 7.710 49.854 -5.502 60 60.125 6.566 59.875 -4.799 70 70.100 5.203 69.900 -3.878 80 80.071 3.655 79.929 -2.772 90 90.038 1.927 89.962 -1.485 95 95.019 0.990 94.981 -0.769 100 100.000 -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 - Aerospaceweb.org: NACA Airfoil Series — web — Publisher's page; dimensions are facts — https://aerospaceweb.org/question/airfoils/q0041.shtml - 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 Free files (Xem Studio Design License, Xem Studio; STEP + STL, 1 parts): https://xemstudio.com/files/hardware/naca-23015-airfoil/index.json API: https://xemstudio.com/api/geometry?object=naca-23015-airfoil