{
 "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-0015-airfoil",
 "name": "NACA 0015 airfoil",
 "kind": "standard",
 "category": "Airfoils",
 "group": "NACA 4-digit",
 "year": null,
 "question": "What is the exact shape of the NACA 0015 airfoil, and what do the digits mean?",
 "tags": [
  "airfoil",
  "naca",
  "wing section",
  "rc plane",
  "aerodynamics",
  "symmetric airfoil"
 ],
 "aliases": [
  "NACA 0015",
  "NACA 0015 airfoil",
  "NACA 0015 coordinates",
  "NACA 0015 dat",
  "NACA 0015 profile",
  "NACA 0015 DXF",
  "NACA 0015 STEP",
  "NACA 0015 STL",
  "perfil NACA 0015",
  "Profil NACA 0015",
  "naca0015",
  "NACA 0015 wing section",
  "15 percent symmetric airfoil",
  "thick symmetric airfoil",
  "3d plane airfoil"
 ],
 "overall_mm": {
  "length": 100,
  "width": 20,
  "height": 15
 },
 "official_cad": false,
 "xem_status": "free-files",
 "les": false,
 "free_files": 1,
 "url": "https://xemstudio.com/objects/naca-0015-airfoil/",
 "sheet_txt": "https://xemstudio.com/objects/naca-0015-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": 15
  },
  "notes": [
   "NACA 0015 is a 15% thick symmetric 4-digit section (NASA TM-4741 designation). Like all symmetric sections it has zero lift at zero angle and zero moment about the a.c. (Virginia Tech Appendix A).",
   "Thicker sections give a deeper spar and gentler stall; NACA data on the 2415 vs 2412 show thickening from 12% to 15% slightly increases drag and slightly lowers CLmax (Virginia Tech Appendix A).",
   "NACA 4-digit sections have good stall behaviour, small centre-of-pressure movement and low roughness sensitivity, but a low CLmax, relatively high drag and high pitching moment (Aerospaceweb summary).",
   "NACA 0015: symmetric, 15 % 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.",
   "Max thickness: 15% chord (from designation) (NASA TM-4741)",
   "Camber: 0 (symmetric) (NASA TM-4741)",
   "Zero-lift angle: 0 deg (symmetric section) (Virginia Tech Appendix A)",
   "Moment about a.c.: zero (symmetric; c.p. = a.c.) (Virginia Tech Appendix A)",
   "Effect of 12% -> 15% thickness (2412 vs 2415): drag slightly up, CLmax slightly down (Virginia Tech Appendix A)",
   "4-digit code: 1st digit max camber %c; 2nd digit camber position in tenths c; last two thickness %c (NASA TM-4741; Aerospaceweb)",
   "Thickness equation (t/c = 0.20 basis): y/c = 0.2969 sqrt(x) - 0.1260 x - 0.3516 x^2 + 0.2843 x^3 - 0.1015 x^4, scaled by (t/c)/0.20 (NASA TM-4741)"
  ],
  "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",
     "2.367",
     "1.250",
     "-2.367"
    ],
    [
     "2.5",
     "2.500",
     "3.268",
     "2.500",
     "-3.268"
    ],
    [
     "5",
     "5.000",
     "4.443",
     "5.000",
     "-4.443"
    ],
    [
     "7.5",
     "7.500",
     "5.250",
     "7.500",
     "-5.250"
    ],
    [
     "10",
     "10.000",
     "5.853",
     "10.000",
     "-5.853"
    ],
    [
     "15",
     "15.000",
     "6.681",
     "15.000",
     "-6.681"
    ],
    [
     "20",
     "20.000",
     "7.172",
     "20.000",
     "-7.172"
    ],
    [
     "25",
     "25.000",
     "7.426",
     "25.000",
     "-7.426"
    ],
    [
     "30",
     "30.000",
     "7.501",
     "30.000",
     "-7.501"
    ],
    [
     "40",
     "40.000",
     "7.250",
     "40.000",
     "-7.250"
    ],
    [
     "50",
     "50.000",
     "6.608",
     "50.000",
     "-6.608"
    ],
    [
     "60",
     "60.000",
     "5.684",
     "60.000",
     "-5.684"
    ],
    [
     "70",
     "70.000",
     "4.542",
     "70.000",
     "-4.542"
    ],
    [
     "80",
     "80.000",
     "3.214",
     "80.000",
     "-3.214"
    ],
    [
     "90",
     "90.000",
     "1.706",
     "90.000",
     "-1.706"
    ],
    [
     "95",
     "95.000",
     "0.880",
     "95.000",
     "-0.880"
    ],
    [
     "100",
     "100.000",
     "-0.000",
     "100.000",
     "0.000"
    ]
   ]
  }
 },
 "sheet_text": "NACA 0015 airfoil — dimension sheet\nSource: Xem Studio, https://xemstudio.com/objects/naca-0015-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 15.0\n- NACA 0015 is a 15% thick symmetric 4-digit section (NASA TM-4741 designation). Like all symmetric sections it has zero lift at zero angle and zero moment about the a.c. (Virginia Tech Appendix A).\n- Thicker sections give a deeper spar and gentler stall; NACA data on the 2415 vs 2412 show thickening from 12% to 15% slightly increases drag and slightly lowers CLmax (Virginia Tech Appendix A).\n- NACA 4-digit sections have good stall behaviour, small centre-of-pressure movement and low roughness sensitivity, but a low CLmax, relatively high drag and high pitching moment (Aerospaceweb summary).\n- NACA 0015: symmetric, 15 % 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- Max thickness: 15% chord (from designation) (NASA TM-4741)\n- Camber: 0 (symmetric) (NASA TM-4741)\n- Zero-lift angle: 0 deg (symmetric section) (Virginia Tech Appendix A)\n- Moment about a.c.: zero (symmetric; c.p. = a.c.) (Virginia Tech Appendix A)\n- Effect of 12% -> 15% thickness (2412 vs 2415): drag slightly up, CLmax slightly down (Virginia Tech Appendix A)\n- 4-digit code: 1st digit max camber %c; 2nd digit camber position in tenths c; last two thickness %c (NASA TM-4741; Aerospaceweb)\n- Thickness equation (t/c = 0.20 basis): y/c = 0.2969 sqrt(x) - 0.1260 x - 0.3516 x^2 + 0.2843 x^3 - 0.1015 x^4, scaled by (t/c)/0.20 (NASA TM-4741)\n\nx (% chord)  upper x  upper y  lower x  lower y\n0  0.000  0.000  0.000  0.000\n1.25  1.250  2.367  1.250  -2.367\n2.5  2.500  3.268  2.500  -3.268\n5  5.000  4.443  5.000  -4.443\n7.5  7.500  5.250  7.500  -5.250\n10  10.000  5.853  10.000  -5.853\n15  15.000  6.681  15.000  -6.681\n20  20.000  7.172  20.000  -7.172\n25  25.000  7.426  25.000  -7.426\n30  30.000  7.501  30.000  -7.501\n40  40.000  7.250  40.000  -7.250\n50  50.000  6.608  50.000  -6.608\n60  60.000  5.684  60.000  -5.684\n70  70.000  4.542  70.000  -4.542\n80  80.000  3.214  80.000  -3.214\n90  90.000  1.706  90.000  -1.706\n95  95.000  0.880  95.000  -0.880\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- NASA Langley (Ladson et al.), NASA TM-4741: Computer Program to Obtain Ordinates for NACA Airfoils — web — Publisher's page; dimensions are facts — https://www.pdas.com/refs/tm4741.pdf\n- Virginia Tech Pressbooks (data from Abbott & von Doenhoff, NACA): Appendix A: Airfoil Data — web — Publisher's page; dimensions are facts — https://pressbooks.lib.vt.edu/aerodynamics/?p=52\n- Aerospaceweb.org: NACA Airfoil Series — web — Publisher's page; dimensions are facts — https://aerospaceweb.org/question/airfoils/q0041.shtml\n\nFree files (Xem Studio Design License, Xem Studio; STEP + STL, 1 parts): https://xemstudio.com/files/hardware/naca-0015-airfoil/index.json\nAPI: https://xemstudio.com/api/geometry?object=naca-0015-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
  },
  {
   "publisher": "NASA Langley (Ladson et al.), NASA TM-4741",
   "title": "Computer Program to Obtain Ordinates for NACA Airfoils",
   "url": "https://www.pdas.com/refs/tm4741.pdf",
   "formats": [
    "web"
   ],
   "license": "Publisher's page; dimensions are facts",
   "license_verified": true,
   "hosted": false
  },
  {
   "publisher": "Virginia Tech Pressbooks (data from Abbott & von Doenhoff, NACA)",
   "title": "Appendix A: Airfoil Data",
   "url": "https://pressbooks.lib.vt.edu/aerodynamics/?p=52",
   "formats": [
    "web"
   ],
   "license": "Publisher's page; dimensions are facts",
   "license_verified": true,
   "hosted": false
  },
  {
   "publisher": "Aerospaceweb.org",
   "title": "NACA Airfoil Series",
   "url": "https://aerospaceweb.org/question/airfoils/q0041.shtml",
   "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-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": "0012 or 0015?",
   "a": "0015 is thicker (stiffer spar) with slightly more drag and slightly less CLmax, per the 2412/2415 comparison (Virginia Tech)."
  },
  {
   "q": "How thick is the NACA 0015?",
   "a": "Maximum thickness 15.00 % of chord at 29.9 % chord: 15.00 mm on a 100 mm chord."
  },
  {
   "q": "Where is the NACA 0015'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-0015-airfoil-section-100mm-chord",
   "formats": [
    "step",
    "stl"
   ],
   "price_usd": 0,
   "license": "Xem Studio Design License",
   "step": "https://xemstudio.com/files/hardware/naca-0015-airfoil/naca-0015-airfoil-section-100mm-chord.step",
   "stl": "https://xemstudio.com/files/hardware/naca-0015-airfoil/naca-0015-airfoil-section-100mm-chord.stl",
   "note": "NACA 0015 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-0015-airfoil/index.md"
}