Selig S1210 airfoil — dimension sheet
Source: Xem Studio, https://xemstudio.com/objects/s1210-airfoil/  (sheet CC BY 4.0; files Xem Studio Design License, https://xemstudio.com/license/)
Basis: Coordinates from the UIUC Airfoil Coordinates Database; thickness, camber and section by Xem Studio
Catalog version: 2026-10-20

Overall (mm): length 100.0, width 20.0, height 12.0
- Selig S1210: Michael Selig (S series). Maximum thickness 12.00 % of chord at 21.5 % chord; maximum camber 7.20 % of chord at 51.1 % chord.
- Coordinates from the UIUC Airfoil Coordinates Database (M. Selig, UIUC Applied Aerodynamics Group), file s1210.dat, titled 'S1210 12%'. 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  12.00 % chord at 21.5 % chord  computed from the UIUC coordinates
Max camber  7.20 % chord at 51.1 % chord  computed from the UIUC coordinates
Published points  81 (45 upper, 37 lower, shared leading edge)  UIUC coordinates
Trailing edge as published  sharp (closed)  UIUC coordinates
y at x = 1.25 % chord  upper +2.767 / lower -1.123 % chord  linear between the published points (UIUC coordinates)
y at x = 2.5 % chord  upper +4.077 / lower -1.389 % chord  linear between the published points (UIUC coordinates)
y at x = 5 % chord  upper +5.908 / lower -1.680 % chord  linear between the published points (UIUC coordinates)
y at x = 7.5 % chord  upper +7.196 / lower -1.797 % chord  linear between the published points (UIUC coordinates)
y at x = 10 % chord  upper +8.192 / lower -1.823 % chord  linear between the published points (UIUC coordinates)
y at x = 15 % chord  upper +9.718 / lower -1.655 % chord  linear between the published points (UIUC coordinates)
y at x = 20 % chord  upper +10.790 / lower -1.169 % chord  linear between the published points (UIUC coordinates)
y at x = 25 % chord  upper +11.533 / lower -0.396 % chord  linear between the published points (UIUC coordinates)
y at x = 30 % chord  upper +11.968 / lower +0.433 % chord  linear between the published points (UIUC coordinates)
y at x = 40 % chord  upper +11.909 / lower +2.022 % chord  linear between the published points (UIUC coordinates)
y at x = 50 % chord  upper +11.066 / lower +3.332 % chord  linear between the published points (UIUC coordinates)
y at x = 60 % chord  upper +9.788 / lower +4.239 % chord  linear between the published points (UIUC coordinates)
y at x = 70 % chord  upper +8.199 / lower +4.643 % chord  linear between the published points (UIUC coordinates)
y at x = 80 % chord  upper +6.295 / lower +4.382 % chord  linear between the published points (UIUC coordinates)
y at x = 90 % chord  upper +3.964 / lower +3.240 % chord  linear between the published points (UIUC coordinates)
y at x = 95 % chord  upper +2.473 / lower +2.112 % chord  linear between the published points (UIUC coordinates)
Coordinates source  UIUC Airfoil Coordinates Database: s1210.dat ('S1210 12%')  UIUC Applied Aerodynamics Group (M. Selig)

Files elsewhere (not hosted by Xem Studio; license as stated by the publisher):
- UIUC Applied Aerodynamics Group (M. Selig): UIUC Airfoil Coordinates Database: s1210.dat ('S1210 12%') — web — UIUC Airfoil Coordinates Database, public research data; coordinates are facts, cited and linked, not rehosted — https://m-selig.ae.illinois.edu/ads/coord/s1210.dat
- UIUC Applied Aerodynamics Group (M. Selig): UIUC Airfoil Coordinates Database (original: Michael Selig (S series)) — web — UIUC Airfoil Coordinates Database, public research data; coordinates are facts, cited and linked, not rehosted — https://m-selig.ae.illinois.edu/ads/coord_database.html

Free files (Xem Studio Design License, Xem Studio; STEP + STL, 1 parts): https://xemstudio.com/files/hardware/s1210-airfoil/index.json
API: https://xemstudio.com/api/geometry?object=s1210-airfoil