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Airfoil database search (NACA 5 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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(naca22112-jf) NACA 22112

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NACA 22112NACA 22112 5 digit reflex airfoil
Max thickness 12% at 29.5% chord
Max camber 0.8% at 9.6% chord
Source Javafoil generated

(naca23012-il) NACA 23012 12%

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NACA 23012  12%NACA 23012 airfoil
Max thickness 12% at 29.8% chord
Max camber 1.8% at 12.7% chord
Source UIUC Airfoil Coordinates Database

(naca23015-il) NACA 23015

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NACA 23015NACA 23015 airfoil
Max thickness 15% at 30% chord
Max camber 1.8% at 15% chord
Source UIUC Airfoil Coordinates Database

(naca23018-il) NACA 23018

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NACA 23018NACA 23018 airfoil
Max thickness 18% at 30% chord
Max camber 1.8% at 15% chord
Source UIUC Airfoil Coordinates Database

(naca23021-il) NACA 23021

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NACA 23021NACA 23021 airfoil
Max thickness 21% at 30% chord
Max camber 1.9% at 10% chord
Source UIUC Airfoil Coordinates Database

(naca23024-il) NACA 23024

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NACA 23024NACA 23024 airfoil
Max thickness 24% at 30.3% chord
Max camber 2.9% at 1.3% chord
Source UIUC Airfoil Coordinates Database

(naca23112-jf) NACA 23112

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NACA 23112NACA 23112 5 digit reflex airfoil
Max thickness 12% at 29.5% chord
Max camber 1.2% at 14.7% chord
Source Javafoil generated

(naca24112-jf) NACA 24112

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NACA 24112NACA 24112 5 digit reflex airfoil
Max thickness 12% at 29.4% chord
Max camber 1.7% at 20.6% chord
Source Javafoil generated

(naca25112-jf) NACA 25112

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NACA 25112NACA 25112 5 digit reflex airfoil
Max thickness 12% at 29.5% chord
Max camber 2% at 27.2% chord
Source Javafoil generated
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