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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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(n66021-il) NACA 66-021 AIRFOIL

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NACA 66-021 AIRFOILNACA 66(4)-021 airfoil
Max thickness 21% at 45% chord
Max camber 0% at 0% 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

(naca000834-il) NACA 0008-34

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NACA 0008-34NACA 0008-34 airfoil
Max thickness 8% at 40% 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

(naca001034-il) NACA 0010-34

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NACA 0010-34NACA 0010-34 airfoil
Max thickness 10% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001035-il) NACA 0010-35

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NACA 0010-35NACA 0010-35 airfoil
Max thickness 10% at 50% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001064-il) NACA 0010-64

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NACA 0010-64NACA 0010-64 airfoil
Max thickness 10% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001065-il) NACA 0010-65

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NACA 0010-65NACA 0010-65 airfoil
Max thickness 10% at 50% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001066-il) NACA 0010-66

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NACA 0010-66NACA 0010-66 airfoil
Max thickness 10% at 60% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
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