NREL S809 airfoil — dimension sheet Source: Xem Studio, https://xemstudio.com/objects/nrel-s809-airfoil/ (sheet CC BY 4.0; files Xem Studio Design License, https://xemstudio.com/license/) Basis: Coordinates from NREL/SR-440-6918 Table 2; thickness, camber and section by Xem Studio Catalog version: 2026-10-20 Overall (mm): length 100.0, width 20.0, height 20.96 - NREL S809: D. M. Somers, for NREL (wind-turbine airfoil). Maximum thickness 20.96 % of chord at 38.2 % chord; maximum camber 0.96 % of chord at 82.3 % chord. - Coordinates from Table 2 of D.M. Somers, 'Design and Experimental Results for the S809 Airfoil' (NREL/SR-440-6918, 1997). The table starts just after the leading edge; the chord-line origin (0, 0) is used as the leading-edge point. Thickness and camber are computed by Xem Studio from those points (vertical distance at equal x, linear between points). - The published trailing edge is sharp, so the section uses it as printed. - 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. parameter value source Max thickness 20.96 % chord at 38.2 % chord computed from NREL/SR-440-6918 Table 2 Max camber 0.96 % chord at 82.3 % chord computed from NREL/SR-440-6918 Table 2 Published points 62 (32 upper, 31 lower, shared leading edge, the (0, 0) leading edge added) NREL/SR-440-6918 Table 2 Trailing edge as published sharp (closed) NREL/SR-440-6918 Table 2 y at x = 1.25 % chord upper +1.787 / lower -1.475 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 2.5 % chord upper +2.705 / lower -2.254 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 5 % chord upper +4.069 / lower -3.492 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 7.5 % chord upper +5.104 / lower -4.569 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 10 % chord upper +5.951 / lower -5.544 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 15 % chord upper +7.300 / lower -7.230 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 20 % chord upper +8.332 / lower -8.594 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 25 % chord upper +9.114 / lower -9.665 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 30 % chord upper +9.651 / lower -10.434 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 40 % chord upper +10.106 / lower -10.804 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 50 % chord upper +9.500 / lower -9.350 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 60 % chord upper +7.724 / lower -6.819 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 70 % chord upper +5.771 / lower -4.232 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 80 % chord upper +3.900 / lower -2.014 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 90 % chord upper +2.044 / lower -0.439 % chord linear between the published points (NREL/SR-440-6918 Table 2) y at x = 95 % chord upper +0.996 / lower -0.019 % chord linear between the published points (NREL/SR-440-6918 Table 2) Coordinates source Design and Experimental Results for the S809 Airfoil, NREL/SR-440-6918 (1997), Table 2 (coordinates) NREL (D.M. Somers) Files elsewhere (not hosted by Xem Studio; license as stated by the publisher): - NREL (D.M. Somers): Design and Experimental Results for the S809 Airfoil, NREL/SR-440-6918 (1997), Table 2 (coordinates) — web — US Government-sponsored report; coordinates are facts — https://www.osti.gov/biblio/437668 Free files (Xem Studio Design License, Xem Studio; STEP + STL, 1 parts): https://xemstudio.com/files/hardware/nrel-s809-airfoil/index.json API: https://xemstudio.com/api/geometry?object=nrel-s809-airfoil