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NACA 63-412 airfoil

Name: NACA 63-412 airfoil dimension sheet
Creator: Xem Studio
License: https://creativecommons.org/licenses/by/4.0/

What is the exact shape of the NACA 63-412 airfoil? · Standard part · basis: Coordinates from the UIUC Airfoil Coordinates Database; thickness, camber and section by Xem Studio

Also called: naca 63-412, naca 63412, naca63412, 63-412, naca 6 series, NACA 63-412 coordinates, NACA 63-412 dat, NACA 63-412 STEP, NACA 63-412 STL, NACA 63-412 profile

Exact dimensions. True size, with no printing tolerance added.

length: 100.0 mm
width: 20.0 mm
height: 12.0 mm

Notes

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.

NACA 63-412 airfoil size chart

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)

Where the files are

Other publishers' files are linked, not hosted. "verify" = check the license at the link before commercial use.

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
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

Free files

★ Free files 1 parts. Xem Studio design: free to use, print and sell things from; not to be republished as files. Xem Studio Design License. index.json

naca-63-412-airfoil-section-100mm-chord

NACA 63-412 section, 100 mm chord × 20 mm span, 50 points from the published coordinates, single trailing-edge point (scale to your chord)

STEP · STL

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Plain text: sheet.txt · JSON: /api/geometry?object=naca-63-412-airfoil

NACA 63-412 airfoil, isometric render of a generated part — Render of naca-63-412-airfoil-section-100mm-chord from the free STEP; not to scale.

Fits with

Free

NACA 2412 airfoil, isometric render of a generated part

NACA 2412 airfoil100.0×20.0×12.0 mm★ 1 file Free

NACA 0012 airfoil, isometric render of a generated part

NACA 0012 airfoil100.0×20.0×12.0 mm★ 1 file

Questions

How thick is the NACA 63-412?

Maximum thickness 12.00 % of chord at 34.9 % chord: 12.00 mm on a 100 mm chord (computed from the UIUC coordinates).

How much camber does the NACA 63-412 have?

Maximum camber 2.20 % of chord at 50.0 % chord (computed from the UIUC coordinates).

How do I use it for my wing?

Scale the 100 mm section to your chord (e.g. 180 mm chord = 180 % scale), then extrude or loft between root and tip sections. For a tapered wing, scale a root and a tip copy and loft between them.