Airfoil database search

Search the 1638 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.

(m4-il) NACA M4 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-4 airfoil Max thickness 6.3% at 30% chord Max camber 2.2% at 30% chord Source UIUC Airfoil Coordinates Database
(fx80080-il) WORTMANN FX 80-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 80-080 airfoil Max thickness 8.1% at 40.2% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(ag24-il) AG24 Bubble Dancer DLG by Mark Drela		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG24 airfoil used on the Bubble Dancer R/C DLG Max thickness 8.4% at 26% chord Max camber 2.2% at 46.9% chord Source UIUC Airfoil Coordinates Database
(s828-nr) NREL's S828 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S828 tip 16.0% Dia=40 to 50 m Re=3.0E+6 Clmax(S)=0.90 Clmax(R)=0.89 Restrained max lift coef Max thickness 16% at 47.1% chord Max camber 2.2% at 47.1% chord Source NWTC National WInd Technology Center
(ag19-il) AG19		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG19 airfoil Max thickness 5.4% at 20.6% chord Max camber 2.2% at 44.2% chord Source UIUC Airfoil Coordinates Database
(s827-nr) NREL's S827 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S827 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.00 Clmax(R)=0.99 Restrained max lift coef Max thickness 21% at 44.9% chord Max camber 2.2% at 68% chord Source NWTC National WInd Technology Center
(goe563-il) GOE 563 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 563 airfoil Max thickness 8.9% at 29.8% chord Max camber 2.2% at 49.8% chord Source UIUC Airfoil Coordinates Database
(ag18-il) AG18		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG18 airfoil Max thickness 5.9% at 20.7% chord Max camber 2.2% at 44.1% chord Source UIUC Airfoil Coordinates Database
(sd2030-il) SD2030-086-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD2030 low Reynolds number airfoil Max thickness 8.6% at 35.5% chord Max camber 2.2% at 45.3% chord Source UIUC Airfoil Coordinates Database
(naca634421-il) NACA 63(4)-421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(4)-421 airfoil Max thickness 21% at 34.8% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database

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