NACA 63-412 airfoil — dimension sheet
Source: Xem Studio, https://xemstudio.com/objects/naca-63-412-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
- NACA 63-412: NACA 6-series (tabulated in NACA Report 824, Abbott, von Doenhoff & Stivers, 1945). Maximum thickness 12.00 % of chord at 34.9 % chord; maximum camber 2.20 % of chord at 50.0 % chord.
- Coordinates from the UIUC Airfoil Coordinates Database (M. Selig, UIUC Applied Aerodynamics Group), file n63412.dat, titled 'NACA 63-412 AIRFOIL'. 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 34.9 % chord  computed from the UIUC coordinates
Max camber  2.20 % chord at 50.0 % chord  computed from the UIUC coordinates
Published points  51 (26 upper, 26 lower, shared leading edge)  UIUC coordinates
Trailing edge as published  sharp (closed)  UIUC coordinates
y at x = 1.25 % chord  upper +1.846 / lower -1.191 % chord  linear between the published points (UIUC coordinates)
y at x = 2.5 % chord  upper +2.567 / lower -1.636 % chord  linear between the published points (UIUC coordinates)
y at x = 5 % chord  upper +3.636 / lower -2.219 % chord  linear between the published points (UIUC coordinates)
y at x = 7.5 % chord  upper +4.456 / lower -2.639 % chord  linear between the published points (UIUC coordinates)
y at x = 10 % chord  upper +5.123 / lower -2.960 % chord  linear between the published points (UIUC coordinates)
y at x = 15 % chord  upper +6.180 / lower -3.422 % chord  linear between the published points (UIUC coordinates)
y at x = 20 % chord  upper +6.956 / lower -3.731 % chord  linear between the published points (UIUC coordinates)
y at x = 25 % chord  upper +7.514 / lower -3.912 % chord  linear between the published points (UIUC coordinates)
y at x = 30 % chord  upper +7.878 / lower -3.982 % chord  linear between the published points (UIUC coordinates)
y at x = 40 % chord  upper +8.059 / lower -3.780 % chord  linear between the published points (UIUC coordinates)
y at x = 50 % chord  upper +7.567 / lower -3.164 % chord  linear between the published points (UIUC coordinates)
y at x = 60 % chord  upper +6.568 / lower -2.273 % chord  linear between the published points (UIUC coordinates)
y at x = 70 % chord  upper +5.166 / lower -1.256 % chord  linear between the published points (UIUC coordinates)
y at x = 80 % chord  upper +3.506 / lower -0.302 % chord  linear between the published points (UIUC coordinates)
y at x = 90 % chord  upper +1.748 / lower +0.329 % chord  linear between the published points (UIUC coordinates)
y at x = 95 % chord  upper +0.885 / lower +0.328 % chord  linear between the published points (UIUC coordinates)
Coordinates source  UIUC Airfoil Coordinates Database: n63412.dat ('NACA 63-412 AIRFOIL')  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: n63412.dat ('NACA 63-412 AIRFOIL') — web — UIUC Airfoil Coordinates Database, public research data; coordinates are facts, cited and linked, not rehosted — https://m-selig.ae.illinois.edu/ads/coord/n63412.dat
- UIUC Applied Aerodynamics Group (M. Selig): UIUC Airfoil Coordinates Database (original: NACA 6-series (tabulated in NACA Report 824, Abbott, von Doenhoff & Stivers, 1945)) — 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/naca-63-412-airfoil/index.json
API: https://xemstudio.com/api/geometry?object=naca-63-412-airfoil