NACA 23012 airfoil — dimension sheet Source: Xem Studio, https://xemstudio.com/objects/naca-23012-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 23012 uses the 230 camber line: design lift coefficient 0.3 with maximum camber far forward at 15% chord, and 12% thickness (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). - Aerospaceweb notes 5-digit sections were used on piston bombers and transports. - NACA 23012: 5-digit 230 mean line (design lift coefficient 0.3, camber peak at 15 % chord), 12 % 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: 12% chord (designation) x (% chord) upper x upper y lower x lower y 0 0.000 0.000 0.000 0.000 1.25 0.763 2.187 1.737 -1.474 2.5 1.916 3.214 3.084 -1.883 5 4.427 4.663 5.573 -2.353 7.5 7.051 5.667 7.949 -2.684 10 9.711 6.375 10.289 -2.973 15 15.000 7.184 15.000 -3.506 20 20.126 7.503 19.874 -3.969 25 25.131 7.596 24.869 -4.283 30 30.132 7.545 29.868 -4.453 40 40.128 7.123 39.872 -4.473 50 50.117 6.389 49.883 -4.181 60 60.100 5.429 59.900 -3.663 70 70.080 4.295 69.920 -2.970 80 80.057 3.013 79.943 -2.129 90 90.030 1.586 89.970 -1.144 95 95.016 0.814 94.984 -0.593 100 100.000 -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 Free files (Xem Studio Design License, Xem Studio; STEP + STL, 1 parts): https://xemstudio.com/files/hardware/naca-23012-airfoil/index.json API: https://xemstudio.com/api/geometry?object=naca-23012-airfoil