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Airfoil database list (N).

NACA 64A410 to NACA 66-209

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(naca64a410-il) NACA 64A410

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NACA 64A410NACA 64A410 airfoil
Max thickness 10% at 39.9% chord
Max camber 2.7% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca651212-il) NACA 65(1)-212

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NACA 65(1)-212NACA 65(1)-212 airfoil
Max thickness 12% at 40% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca651212a06-il) NACA 65(1)-212 a=0.6

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NACA 65(1)-212 a=0.6NACA 65(1)-212 a=0.6 airfoil
Max thickness 12% at 40% chord
Max camber 1.5% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca651412-il) NACA 65(1)-412

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NACA 65(1)-412NACA 65(1)-412 airfoil
Max thickness 12% at 39.9% chord
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca65206-il) NACA 65-206

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NACA 65-206NACA 65-206 airfoil
Max thickness 6% at 40% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca65209-il) NACA 65-209

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NACA 65-209NACA 65-209 airfoil
Max thickness 9% at 40% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca65210-il) NACA 65-210

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NACA 65-210NACA 65-210 airfoil
Max thickness 10% at 40% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca652215-il) NACA 65(2)-215

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NACA 65(2)-215NACA 65(2)-215 airfoil
Max thickness 15% at 40% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca652415-il) NACA 65(2)-415

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NACA 65(2)-415NACA 65(2)-415 airfoil
Max thickness 15% at 39.9% chord
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca652415a05-il) NACA 65(2)-415 a=0.5

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NACA 65(2)-415 a=0.5NACA 65(2)-415 a=0.5 airfoil
Max thickness 15% at 39.9% chord
Max camber 3% at 45% chord
Source UIUC Airfoil Coordinates Database

(naca653218-il) NACA 65(3)-218

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NACA 65(3)-218NACA 65(3)-218 airfoil
Max thickness 18% at 39.9% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca653618-il) NACA 65(3)-618

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NACA 65(3)-618NACA 65(3)-618 airfoil
Max thickness 18% at 39.8% chord
Max camber 3.3% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca65410-il) NACA 65-410

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NACA 65-410NACA 65-410 airfoil
Max thickness 10% at 39.9% chord
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca654221-il) NACA 65(4)-221

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NACA 65(4)-221NACA 65(4)-221 airfoil
Max thickness 21% at 39.9% chord
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(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
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