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Airfoil database search (NACA 4 digit)

Search the 1629 airfoils available in the databases filtering by name, thickness and camber. Click on an airfoil image to display a larger preview picture. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.

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(n0009sm-il) NACA-0009 9.0% smoothed

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NACA-0009 9.0% smoothedNACA 0009 airfoil (smoothed)
Max thickness 9% at 30.9% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(n0012-il) NACA 0012 AIRFOILS

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NACA 0012 AIRFOILSNACA 0012 airfoil
Max thickness 12% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(n2414-il) NACA 2414

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NACA 2414NACA 2414 airfoil
Max thickness 14% at 29.5% chord
Max camber 2% at 39.6% chord
Source UIUC Airfoil Coordinates Database

(n2415-il) NACA 2415

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NACA 2415NACA 2415 airfoil
Max thickness 15% at 29.5% chord
Max camber 2% at 39.6% chord
Source UIUC Airfoil Coordinates Database

(n6409-il) NACA6409 9%

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NACA6409 9%NACA 6409
Max thickness 9% at 29.3% chord
Max camber 6% at 39.6% chord
Source UIUC Airfoil Coordinates Database

(naca0006-il) NACA 0006

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NACA 0006NACA 0006 airfoil
Max thickness 6% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca0008-il) NACA 0008

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NACA 0008NACA 0008 airfoil
Max thickness 8% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca0010-il) NACA 0010

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NACA 0010NACA 0010 airfoil
Max thickness 10% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca0012h-sa) NACA0012H for VAWT from Sandia report SAND80-2114

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NACA0012H for VAWT from Sandia report SAND80-2114Modified Naca 0012 airfoil for Sandia VAWT tests
Max thickness 12.2% at 22.5% chord
Max camber 0% at 0% chord
Source Sandia National Laboratories

(naca0015-il) NACA 0015

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NACA 0015NACA 0015 airfoil
Max thickness 15% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
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