{
 "version": "2026-10-20",
 "license": "Dimension sheets: CC BY 4.0. Standard and published-size files: CC BY 4.0. Xem Studio's own designs (files_license = Xem Studio Design License): free to use and sell things from, not to redistribute as files — https://xemstudio.com/license/. Other publishers' files: their own license, linked beside them.",
 "slug": "naca-63-412-airfoil",
 "name": "NACA 63-412 airfoil",
 "kind": "standard",
 "category": "Airfoils",
 "group": "NACA 6-series",
 "year": null,
 "question": "What is the exact shape of the NACA 63-412 airfoil?",
 "tags": [
  "airfoil",
  "wing section",
  "rc plane",
  "aerodynamics",
  "cambered airfoil"
 ],
 "aliases": [
  "naca 63-412",
  "naca 63412",
  "naca63412",
  "63-412",
  "naca 6 series",
  "NACA 63-412 airfoil",
  "NACA 63-412 coordinates",
  "NACA 63-412 dat",
  "NACA 63-412 STEP",
  "NACA 63-412 STL",
  "NACA 63-412 profile"
 ],
 "overall_mm": {
  "length": 100,
  "width": 20,
  "height": 12
 },
 "official_cad": false,
 "xem_status": "free-files",
 "les": false,
 "free_files": 1,
 "url": "https://xemstudio.com/objects/naca-63-412-airfoil/",
 "sheet_txt": "https://xemstudio.com/objects/naca-63-412-airfoil/sheet.txt",
 "sheet": {
  "basis": "Coordinates from the UIUC Airfoil Coordinates Database; thickness, camber and section by Xem Studio",
  "overall_mm": {
   "length": 100,
   "width": 20,
   "height": 12
  },
  "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."
  ],
  "table": {
   "columns": [
    "parameter",
    "value",
    "source"
   ],
   "rows": [
    [
     "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)"
    ]
   ]
  }
 },
 "sheet_text": "NACA 63-412 airfoil — dimension sheet\nSource: Xem Studio, https://xemstudio.com/objects/naca-63-412-airfoil/  (sheet CC BY 4.0; files Xem Studio Design License, https://xemstudio.com/license/)\nBasis: Coordinates from the UIUC Airfoil Coordinates Database; thickness, camber and section by Xem Studio\nCatalog version: 2026-10-20\n\nOverall (mm): length 100.0, width 20.0, height 12.0\n- 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.\n- 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).\n- The published trailing edge is sharp, so the section uses it as printed.\n- 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.\n\nparameter  value  source\nMax thickness  12.00 % chord at 34.9 % chord  computed from the UIUC coordinates\nMax camber  2.20 % chord at 50.0 % chord  computed from the UIUC coordinates\nPublished points  51 (26 upper, 26 lower, shared leading edge)  UIUC coordinates\nTrailing edge as published  sharp (closed)  UIUC coordinates\ny at x = 1.25 % chord  upper +1.846 / lower -1.191 % chord  linear between the published points (UIUC coordinates)\ny at x = 2.5 % chord  upper +2.567 / lower -1.636 % chord  linear between the published points (UIUC coordinates)\ny at x = 5 % chord  upper +3.636 / lower -2.219 % chord  linear between the published points (UIUC coordinates)\ny at x = 7.5 % chord  upper +4.456 / lower -2.639 % chord  linear between the published points (UIUC coordinates)\ny at x = 10 % chord  upper +5.123 / lower -2.960 % chord  linear between the published points (UIUC coordinates)\ny at x = 15 % chord  upper +6.180 / lower -3.422 % chord  linear between the published points (UIUC coordinates)\ny at x = 20 % chord  upper +6.956 / lower -3.731 % chord  linear between the published points (UIUC coordinates)\ny at x = 25 % chord  upper +7.514 / lower -3.912 % chord  linear between the published points (UIUC coordinates)\ny at x = 30 % chord  upper +7.878 / lower -3.982 % chord  linear between the published points (UIUC coordinates)\ny at x = 40 % chord  upper +8.059 / lower -3.780 % chord  linear between the published points (UIUC coordinates)\ny at x = 50 % chord  upper +7.567 / lower -3.164 % chord  linear between the published points (UIUC coordinates)\ny at x = 60 % chord  upper +6.568 / lower -2.273 % chord  linear between the published points (UIUC coordinates)\ny at x = 70 % chord  upper +5.166 / lower -1.256 % chord  linear between the published points (UIUC coordinates)\ny at x = 80 % chord  upper +3.506 / lower -0.302 % chord  linear between the published points (UIUC coordinates)\ny at x = 90 % chord  upper +1.748 / lower +0.329 % chord  linear between the published points (UIUC coordinates)\ny at x = 95 % chord  upper +0.885 / lower +0.328 % chord  linear between the published points (UIUC coordinates)\nCoordinates source  UIUC Airfoil Coordinates Database: n63412.dat ('NACA 63-412 AIRFOIL')  UIUC Applied Aerodynamics Group (M. Selig)\n\nFiles elsewhere (not hosted by Xem Studio; license as stated by the publisher):\n- 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\n- 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\n\nFree files (Xem Studio Design License, Xem Studio; STEP + STL, 1 parts): https://xemstudio.com/files/hardware/naca-63-412-airfoil/index.json\nAPI: https://xemstudio.com/api/geometry?object=naca-63-412-airfoil\n",
 "sources": [
  {
   "publisher": "UIUC Applied Aerodynamics Group (M. Selig)",
   "title": "UIUC Airfoil Coordinates Database: n63412.dat ('NACA 63-412 AIRFOIL')",
   "url": "https://m-selig.ae.illinois.edu/ads/coord/n63412.dat",
   "formats": [
    "web"
   ],
   "license": "UIUC Airfoil Coordinates Database, public research data; coordinates are facts, cited and linked, not rehosted",
   "license_verified": true,
   "hosted": false
  },
  {
   "publisher": "UIUC Applied Aerodynamics Group (M. Selig)",
   "title": "UIUC Airfoil Coordinates Database (original: NACA 6-series (tabulated in NACA Report 824, Abbott, von Doenhoff & Stivers, 1945))",
   "url": "https://m-selig.ae.illinois.edu/ads/coord_database.html",
   "formats": [
    "web"
   ],
   "license": "UIUC Airfoil Coordinates Database, public research data; coordinates are facts, cited and linked, not rehosted",
   "license_verified": true,
   "hosted": false
  }
 ],
 "xem": {
  "status": "free-files",
  "sheet_free": true,
  "mesh_price_usd": null,
  "step_price_usd": null,
  "tolerance_mm": null
 },
 "related": [
  "naca-2412-airfoil",
  "naca-0012-airfoil"
 ],
 "fits": [],
 "dimensions": "exact (nominal, no printing tolerance)",
 "dimension_rule": "All geometry on Xem Studio is exact (nominal, true size) with no printing tolerance. Where a part meets another part, the object lists its mating features (feature, exact size, what it mates with, fit class: press, slide, run, socket, clamp or designed). Apply your process's allowance to those features only; 'designed' gaps are part of the design and stay as drawn.",
 "mating": [],
 "faq": [
  {
   "q": "How thick is the NACA 63-412?",
   "a": "Maximum thickness 12.00 % of chord at 34.9 % chord: 12.00 mm on a 100 mm chord (computed from the UIUC coordinates)."
  },
  {
   "q": "How much camber does the NACA 63-412 have?",
   "a": "Maximum camber 2.20 % of chord at 50.0 % chord (computed from the UIUC coordinates)."
  },
  {
   "q": "How do I use it for my wing?",
   "a": "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."
  }
 ],
 "files_license": {
  "name": "Xem Studio Design License",
  "holder": "Xem Studio",
  "url": "https://xemstudio.com/license/",
  "note": "Xem Studio's own design: free to use, print, modify and sell things made from it; not to be republished or redistributed as files."
 },
 "offers": [
  {
   "file": "naca-63-412-airfoil-section-100mm-chord",
   "formats": [
    "step",
    "stl"
   ],
   "price_usd": 0,
   "license": "Xem Studio Design License",
   "step": "https://xemstudio.com/files/hardware/naca-63-412-airfoil/naca-63-412-airfoil-section-100mm-chord.step",
   "stl": "https://xemstudio.com/files/hardware/naca-63-412-airfoil/naca-63-412-airfoil-section-100mm-chord.stl",
   "note": "NACA 63-412 section, 100 mm chord × 20 mm span, 50 points from the published coordinates, single trailing-edge point (scale to your chord)"
  }
 ],
 "markdown": "https://xemstudio.com/objects/naca-63-412-airfoil/index.md"
}