{
 "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-0008-airfoil",
 "name": "NACA 0008 airfoil",
 "kind": "standard",
 "category": "Airfoils",
 "group": "NACA 4-digit",
 "year": null,
 "question": "What is the exact shape of the NACA 0008 airfoil, and what do the digits mean?",
 "tags": [
  "airfoil",
  "naca",
  "wing section",
  "rc plane",
  "aerodynamics",
  "symmetric airfoil"
 ],
 "aliases": [
  "NACA 0008",
  "NACA 0008 airfoil",
  "NACA 0008 coordinates",
  "NACA 0008 dat",
  "NACA 0008 profile",
  "NACA 0008 DXF",
  "NACA 0008 STEP",
  "NACA 0008 STL",
  "perfil NACA 0008",
  "Profil NACA 0008",
  "naca0008",
  "NACA 0008 wing section"
 ],
 "overall_mm": {
  "length": 100,
  "width": 20,
  "height": 8
 },
 "official_cad": false,
 "xem_status": "free-files",
 "les": false,
 "free_files": 1,
 "url": "https://xemstudio.com/objects/naca-0008-airfoil/",
 "sheet_txt": "https://xemstudio.com/objects/naca-0008-airfoil/sheet.txt",
 "sheet": {
  "basis": "Computed from the NACA equations (Report 460 / Report 610, restated in NASA TM-4741)",
  "overall_mm": {
   "length": 100,
   "width": 20,
   "height": 8
  },
  "notes": [
   "NACA 0008: symmetric, 8 % thick.",
   "NACA 4-digit: first digit = maximum camber in % of chord, second = its position in tenths of chord, last two = maximum thickness in % of chord (NACA Report 460).",
   "Ordinates are in % of chord from the leading edge, computed from the published equations with the closed-trailing-edge thickness coefficient (−0.1036, as in NASA TM-4741). The original reports use an open trailing edge (−0.1015); the difference is under 0.03 % of chord near the trailing edge.",
   "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": [
    "x (% chord)",
    "upper x",
    "upper y",
    "lower x",
    "lower y"
   ],
   "rows": [
    [
     "0",
     "0.000",
     "0.000",
     "0.000",
     "0.000"
    ],
    [
     "1.25",
     "1.250",
     "1.263",
     "1.250",
     "-1.263"
    ],
    [
     "2.5",
     "2.500",
     "1.743",
     "2.500",
     "-1.743"
    ],
    [
     "5",
     "5.000",
     "2.370",
     "5.000",
     "-2.370"
    ],
    [
     "7.5",
     "7.500",
     "2.800",
     "7.500",
     "-2.800"
    ],
    [
     "10",
     "10.000",
     "3.122",
     "10.000",
     "-3.122"
    ],
    [
     "15",
     "15.000",
     "3.563",
     "15.000",
     "-3.563"
    ],
    [
     "20",
     "20.000",
     "3.825",
     "20.000",
     "-3.825"
    ],
    [
     "25",
     "25.000",
     "3.961",
     "25.000",
     "-3.961"
    ],
    [
     "30",
     "30.000",
     "4.000",
     "30.000",
     "-4.000"
    ],
    [
     "40",
     "40.000",
     "3.867",
     "40.000",
     "-3.867"
    ],
    [
     "50",
     "50.000",
     "3.524",
     "50.000",
     "-3.524"
    ],
    [
     "60",
     "60.000",
     "3.031",
     "60.000",
     "-3.031"
    ],
    [
     "70",
     "70.000",
     "2.422",
     "70.000",
     "-2.422"
    ],
    [
     "80",
     "80.000",
     "1.714",
     "80.000",
     "-1.714"
    ],
    [
     "90",
     "90.000",
     "0.910",
     "90.000",
     "-0.910"
    ],
    [
     "95",
     "95.000",
     "0.469",
     "95.000",
     "-0.469"
    ],
    [
     "100",
     "100.000",
     "-0.000",
     "100.000",
     "0.000"
    ]
   ]
  }
 },
 "sheet_text": "NACA 0008 airfoil — dimension sheet\nSource: Xem Studio, https://xemstudio.com/objects/naca-0008-airfoil/  (sheet CC BY 4.0; files Xem Studio Design License, https://xemstudio.com/license/)\nBasis: Computed from the NACA equations (Report 460 / Report 610, restated in NASA TM-4741)\nCatalog version: 2026-10-20\n\nOverall (mm): length 100.0, width 20.0, height 8.0\n- NACA 0008: symmetric, 8 % thick.\n- NACA 4-digit: first digit = maximum camber in % of chord, second = its position in tenths of chord, last two = maximum thickness in % of chord (NACA Report 460).\n- Ordinates are in % of chord from the leading edge, computed from the published equations with the closed-trailing-edge thickness coefficient (−0.1036, as in NASA TM-4741). The original reports use an open trailing edge (−0.1015); the difference is under 0.03 % of chord near the trailing edge.\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\nx (% chord)  upper x  upper y  lower x  lower y\n0  0.000  0.000  0.000  0.000\n1.25  1.250  1.263  1.250  -1.263\n2.5  2.500  1.743  2.500  -1.743\n5  5.000  2.370  5.000  -2.370\n7.5  7.500  2.800  7.500  -2.800\n10  10.000  3.122  10.000  -3.122\n15  15.000  3.563  15.000  -3.563\n20  20.000  3.825  20.000  -3.825\n25  25.000  3.961  25.000  -3.961\n30  30.000  4.000  30.000  -4.000\n40  40.000  3.867  40.000  -3.867\n50  50.000  3.524  50.000  -3.524\n60  60.000  3.031  60.000  -3.031\n70  70.000  2.422  70.000  -2.422\n80  80.000  1.714  80.000  -1.714\n90  90.000  0.910  90.000  -0.910\n95  95.000  0.469  95.000  -0.469\n100  100.000  -0.000  100.000  0.000\n\nFiles elsewhere (not hosted by Xem Studio; license as stated by the publisher):\n- NACA (NASA Technical Reports Server): Report 460: The characteristics of 78 related airfoil sections from tests in the variable-density wind tunnel (Jacobs, Ward, Pinkerton, 1933) — web — Publisher's page; dimensions are facts — https://ntrs.nasa.gov/citations/19930091108\n- NASA: TM-4741: Computer program to obtain ordinates for NACA airfoils (Ladson, Brooks, Hill, Sproles, 1996) — web — Publisher's page; dimensions are facts — https://www.pdas.com/refs/tm4741.pdf\n\nFree files (Xem Studio Design License, Xem Studio; STEP + STL, 1 parts): https://xemstudio.com/files/hardware/naca-0008-airfoil/index.json\nAPI: https://xemstudio.com/api/geometry?object=naca-0008-airfoil\n",
 "sources": [
  {
   "publisher": "NACA (NASA Technical Reports Server)",
   "title": "Report 460: The characteristics of 78 related airfoil sections from tests in the variable-density wind tunnel (Jacobs, Ward, Pinkerton, 1933)",
   "url": "https://ntrs.nasa.gov/citations/19930091108",
   "formats": [
    "web"
   ],
   "license": "Publisher's page; dimensions are facts",
   "license_verified": true,
   "hosted": false
  },
  {
   "publisher": "NASA",
   "title": "TM-4741: Computer program to obtain ordinates for NACA airfoils (Ladson, Brooks, Hill, Sproles, 1996)",
   "url": "https://www.pdas.com/refs/tm4741.pdf",
   "formats": [
    "web"
   ],
   "license": "Publisher's page; dimensions are facts",
   "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-0006-airfoil",
  "naca-0009-airfoil",
  "naca-0010-airfoil",
  "naca-0012-airfoil",
  "naca-0015-airfoil",
  "naca-0018-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 0008?",
   "a": "Maximum thickness 8.00 % of chord at 29.9 % chord: 8.00 mm on a 100 mm chord."
  },
  {
   "q": "Where is the NACA 0008's camber?",
   "a": "None: it is symmetric (upper and lower surfaces mirror)."
  },
  {
   "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-0008-airfoil-section-100mm-chord",
   "formats": [
    "step",
    "stl"
   ],
   "price_usd": 0,
   "license": "Xem Studio Design License",
   "step": "https://xemstudio.com/files/hardware/naca-0008-airfoil/naca-0008-airfoil-section-100mm-chord.step",
   "stl": "https://xemstudio.com/files/hardware/naca-0008-airfoil/naca-0008-airfoil-section-100mm-chord.stl",
   "note": "NACA 0008 section, 100 mm chord × 20 mm span, closed trailing edge, 160 points from the equations (scale to your chord)"
  }
 ],
 "markdown": "https://xemstudio.com/objects/naca-0008-airfoil/index.md"
}