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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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(naca654421-il) NACA 65(4)-421

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NACA 65(4)-421NACA 65(4)-421 airfoil
Max thickness 21% at 39.9% chord
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca654421a05-il) NACA 65(4)-421 a=0.5

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NACA 65(4)-421 a=0.5NACA 65(4)-421 a=0.5 airfoil
Max thickness 21% at 39.9% chord
Max camber 3% at 45% chord
Source UIUC Airfoil Coordinates Database

(naca66-018-il) NACA 66-018

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NACA 66-018NACA 66-018 airfoil
Max thickness 18% at 45% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca661212-il) NACA 66(1)-212

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NACA 66(1)-212NACA 66(1)-212 airfoil
Max thickness 12% at 45% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca66206-il) NACA 66-206

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NACA 66-206NACA 66-206 airfoil
Max thickness 6% at 45% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca66209-il) NACA 66-209

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NACA 66-209NACA 66-209 airfoil
Max thickness 9% at 45% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca66210-il) NACA 66-210

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NACA 66-210NACA 66-210 airfoil
Max thickness 10% at 45% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca662215-il) NACA 66(2)-215

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NACA 66(2)-215NACA 66(2)-215 airfoil
Max thickness 15% at 45% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca662415-il) NACA 66(2)-415

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NACA 66(2)-415NACA 66(2)-415 airfoil
Max thickness 15% at 45% chord
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca663218-il) NACA 66(3)-218

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NACA 66(3)-218NACA 66(3)-218 airfoil
Max thickness 18% at 45% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
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