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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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(n64012-il) NASA/LANGLEY 64-012 AIRFOIL

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NASA/LANGLEY 64-012 AIRFOILNACA 64(1)-012 airfoil
Max thickness 12% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(n64012a-il) NACA 64-012A AIRFOIL

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NACA 64-012A AIRFOILNACA 64(1)-012A airfoil
Max thickness 12% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(n64015-il) NACA 642-015 AIRFOIL

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NACA 642-015 AIRFOILNACA 64(2)-015 airfoil
Max thickness 15% at 35% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(n64015a-il) NACA 642-015A AIRFOIL

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NACA 642-015A AIRFOILNACA 64(2)-015A airfoil
Max thickness 15% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(n64108-il) NACA 64-108 AIRFOIL

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NACA 64-108 AIRFOILNACA 64-108 airfoil
Max thickness 8% at 40% chord
Max camber 0.6% at 50% chord
Source UIUC Airfoil Coordinates Database

(n64110-il) NACA 64-110 AIRFOIL

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NACA 64-110 AIRFOILNACA 64-110 airfoil
Max thickness 10% at 40% chord
Max camber 0.6% at 50% chord
Source UIUC Airfoil Coordinates Database

(n64212-il) NACA 64(1)-212

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NACA 64(1)-212NACA 64(1)-212 airfoil
Max thickness 12% at 40% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(n64212ma-il) NACA 64(1)-212 MOD A

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NACA 64(1)-212 MOD ANACA-NASA/AMES/Hicks 63(1)-212 MOD A airfoil
Max thickness 12% at 41.2% chord
Max camber 2.5% at 21.5% chord
Source UIUC Airfoil Coordinates Database

(n64212mb-il) NACA 64(1)-212 MOD B

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NACA 64(1)-212 MOD BNACA-NASA/AMES/Hicks 63(1)-212 MOD B airfoil
Max thickness 12% at 34.9% chord
Max camber 1.5% at 9.9% chord
Source UIUC Airfoil Coordinates Database

(n64215-il) NACA 64-215 AIRFOIL

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NACA 64-215 AIRFOILNACA 64(2)-215 airfoil
Max thickness 15% at 34.9% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
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