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Airfoil database search (NACA 6 series)

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

(naca63206-il) NACA 63-206

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NACA 63-206NACA 63-206 airfoil
Max thickness 6% at 35% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca63209-il) NACA 63-209

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NACA 63-209NACA 63-209 airfoil
Max thickness 9% at 35% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca632615-il) NACA 63(2)-615

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NACA 63(2)-615NACA 63(2)-615 airfoil
Max thickness 15% at 34.8% chord
Max camber 3.3% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca632a015-il) NACA 63(2)A-015

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NACA 63(2)A-015NACA 63(2)A-015 airfoil
Max thickness 15% at 37.1% chord
Max camber 1.7% at 14.6% chord
Source UIUC Airfoil Coordinates Database

(naca633018-il) NACA 63(3)-018

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NACA 63(3)-018NACA 63(3)-018 airfoil
Max thickness 18% at 33.9% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca633218-il) NACA 63(3)-218

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NACA 63(3)-218NACA 63(3)-218 airfoil
Max thickness 18% at 34.9% chord
Max camber 1.1% at 24.9% chord
Source UIUC Airfoil Coordinates Database

(naca633418-il) NACA 63

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NACA 63NACA 63
Max thickness 18% at 33.9% chord
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca633618-il) NACA 63(3)-618

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NACA 63(3)-618NACA 63(3)-618 airfoil
Max thickness 18% at 34.7% chord
Max camber 3.3% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca634221-il) NACA 63(4)-221

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NACA 63(4)-221NACA 63(4)-221 airfoil
Max thickness 21% at 34.9% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
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