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Airfoil database search (Symmetrical)

Search the 1636 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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(naca001234-il) NACA 0012-34

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NACA 0012-34NACA 0012-34 airfoil
Max thickness 12% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001264-il) NACA 0012-64

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NACA 0012-64NACA 0012-64 airfoil
Max thickness 12% at 40% 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

(naca0018-il) NACA 0018

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NACA 0018NACA 0018 airfoil
Max thickness 18% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca0021-il) NACA 0021

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NACA 0021NACA 0021 airfoil
Max thickness 21% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca0024-il) NACA 0024

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NACA 0024NACA 0024 airfoil
Max thickness 24% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca16006-il) NACA 16-006

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NACA 16-006NACA 16-006 airfoil
Max thickness 6% at 50% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca16009-il) NACA 16009

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NACA 16009NACA 16009 airfoil
Max thickness 9% at 50% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca16012-il) NACA 16-012

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NACA 16-012NACA 16-012 airfoil
Max thickness 12% at 50% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
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