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Airfoil database search (NACA 4 digit)

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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(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

(naca1408-il) NACA 1408

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NACA 1408NACA 1408 airfoil
Max thickness 8% at 30% chord
Max camber 1% at 40% chord
Source UIUC Airfoil Coordinates Database

(naca1410-il) NACA 1410

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NACA 1410NACA 1410 airfoil
Max thickness 10% at 29.9% chord
Max camber 1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca1412-il) NACA 1412

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NACA 1412NACA 1412 airfoil
Max thickness 12% at 29.9% chord
Max camber 1% at 40% chord
Source UIUC Airfoil Coordinates Database

(naca2408-il) NACA 2408

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NACA 2408NACA 2408 airfoil
Max thickness 8% at 29.9% chord
Max camber 2% at 40% chord
Source UIUC Airfoil Coordinates Database

(naca2410-il) NACA 2410

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NACA 2410NACA 2410 airfoil
Max thickness 10% at 29.9% chord
Max camber 2% at 40% chord
Source UIUC Airfoil Coordinates Database

(naca2411-il) NACA 2.5411

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NACA 2.5411NACA 2411 airfoil
Max thickness 11% at 29.5% chord
Max camber 2.5% at 39.6% chord
Source UIUC Airfoil Coordinates Database

(naca2412-il) NACA 2412

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NACA 2412NACA 2412 airfoil
Max thickness 12% at 30% chord
Max camber 2% at 40% chord
Source UIUC Airfoil Coordinates Database
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