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Airfoil database list (N).

NACA 64A410 to NACA 66-209

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(naca64a410-il) NACA 64A410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 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		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-209 airfoil Max thickness 9% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database