{
 "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-0024-airfoil",
 "name": "NACA 0024 airfoil",
 "kind": "standard",
 "category": "Airfoils",
 "group": "NACA 4-digit",
 "year": null,
 "question": "What is the exact shape of the NACA 0024 airfoil, and what do the digits mean?",
 "tags": [
  "airfoil",
  "naca",
  "wing section",
  "rc plane",
  "aerodynamics",
  "symmetric airfoil"
 ],
 "aliases": [
  "NACA 0024",
  "NACA 0024 airfoil",
  "NACA 0024 coordinates",
  "NACA 0024 dat",
  "NACA 0024 profile",
  "NACA 0024 DXF",
  "NACA 0024 STEP",
  "NACA 0024 STL",
  "perfil NACA 0024",
  "Profil NACA 0024",
  "naca0024",
  "NACA 0024 wing section"
 ],
 "overall_mm": {
  "length": 100,
  "width": 20,
  "height": 24
 },
 "official_cad": false,
 "xem_status": "free-files",
 "les": false,
 "free_files": 1,
 "url": "https://xemstudio.com/objects/naca-0024-airfoil/",
 "sheet_txt": "https://xemstudio.com/objects/naca-0024-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": 24
  },
  "notes": [
   "NACA 0024: symmetric, 24 % 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",
     "3.788",
     "1.250",
     "-3.788"
    ],
    [
     "2.5",
     "2.500",
     "5.229",
     "2.500",
     "-5.229"
    ],
    [
     "5",
     "5.000",
     "7.109",
     "5.000",
     "-7.109"
    ],
    [
     "7.5",
     "7.500",
     "8.400",
     "7.500",
     "-8.400"
    ],
    [
     "10",
     "10.000",
     "9.366",
     "10.000",
     "-9.366"
    ],
    [
     "15",
     "15.000",
     "10.690",
     "15.000",
     "-10.690"
    ],
    [
     "20",
     "20.000",
     "11.475",
     "20.000",
     "-11.475"
    ],
    [
     "25",
     "25.000",
     "11.882",
     "25.000",
     "-11.882"
    ],
    [
     "30",
     "30.000",
     "12.001",
     "30.000",
     "-12.001"
    ],
    [
     "40",
     "40.000",
     "11.600",
     "40.000",
     "-11.600"
    ],
    [
     "50",
     "50.000",
     "10.572",
     "50.000",
     "-10.572"
    ],
    [
     "60",
     "60.000",
     "9.094",
     "60.000",
     "-9.094"
    ],
    [
     "70",
     "70.000",
     "7.267",
     "70.000",
     "-7.267"
    ],
    [
     "80",
     "80.000",
     "5.143",
     "80.000",
     "-5.143"
    ],
    [
     "90",
     "90.000",
     "2.730",
     "90.000",
     "-2.730"
    ],
    [
     "95",
     "95.000",
     "1.408",
     "95.000",
     "-1.408"
    ],
    [
     "100",
     "100.000",
     "-0.000",
     "100.000",
     "0.000"
    ]
   ]
  }
 },
 "sheet_text": "NACA 0024 airfoil — dimension sheet\nSource: Xem Studio, https://xemstudio.com/objects/naca-0024-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 24.0\n- NACA 0024: symmetric, 24 % 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  3.788  1.250  -3.788\n2.5  2.500  5.229  2.500  -5.229\n5  5.000  7.109  5.000  -7.109\n7.5  7.500  8.400  7.500  -8.400\n10  10.000  9.366  10.000  -9.366\n15  15.000  10.690  15.000  -10.690\n20  20.000  11.475  20.000  -11.475\n25  25.000  11.882  25.000  -11.882\n30  30.000  12.001  30.000  -12.001\n40  40.000  11.600  40.000  -11.600\n50  50.000  10.572  50.000  -10.572\n60  60.000  9.094  60.000  -9.094\n70  70.000  7.267  70.000  -7.267\n80  80.000  5.143  80.000  -5.143\n90  90.000  2.730  90.000  -2.730\n95  95.000  1.408  95.000  -1.408\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-0024-airfoil/index.json\nAPI: https://xemstudio.com/api/geometry?object=naca-0024-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-0008-airfoil",
  "naca-0009-airfoil",
  "naca-0010-airfoil",
  "naca-0012-airfoil",
  "naca-0015-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 0024?",
   "a": "Maximum thickness 24.00 % of chord at 29.9 % chord: 24.00 mm on a 100 mm chord."
  },
  {
   "q": "Where is the NACA 0024'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-0024-airfoil-section-100mm-chord",
   "formats": [
    "step",
    "stl"
   ],
   "price_usd": 0,
   "license": "Xem Studio Design License",
   "step": "https://xemstudio.com/files/hardware/naca-0024-airfoil/naca-0024-airfoil-section-100mm-chord.step",
   "stl": "https://xemstudio.com/files/hardware/naca-0024-airfoil/naca-0024-airfoil-section-100mm-chord.stl",
   "note": "NACA 0024 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-0024-airfoil/index.md"
}