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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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(n0011sc-il) NACA/LANGLEY SYMMETRICAL

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NACA/LANGLEY SYMMETRICALNASA/Langley 11% symmetrical supercritical airfoil
Max thickness 11% at 40% 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

(n63010a-il) NACA 63A010 AIRFOIL

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NACA 63A010 AIRFOILNACA 63-010A airfoil
Max thickness 10% at 35% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(n63012a-il) NACA 63012A AIRFOIL

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NACA 63012A AIRFOILNACA 63-012A airfoil
Max thickness 12% at 35% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(n63015a-il) NACA 63-015A AIRFOIL

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NACA 63-015A AIRFOILNACA 63-015A airfoil
Max thickness 15% at 35% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(n64008a-il) NACA 64-008A AIRFOIL

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NACA 64-008A AIRFOILNACA 64-008A airfoil
Max thickness 8% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(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
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