Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

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.

(s829-nr) NREL's S829 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S829 tip 16.0% Dia=20 to 40 m Re=2.0E+6 Clmax(S)=0.70 Clmax(R)=0.68 Restrained max lift coef Max thickness 16% at 48.3% chord Max camber 0.7% at 48.3% chord Source NWTC National WInd Technology Center
(sc20404-il) NASA SC(2)-0404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0404 airfoil (NASA TP-2969) Max thickness 4% at 37% chord Max camber 0.7% at 81% chord Source UIUC Airfoil Coordinates Database
(cap21c-il) CAP 21 (TraCFoil)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAP 21 (TraCFoil) airfoil Max thickness 15.6% at 15.7% chord Max camber 0.6% at 23.9% chord Source UIUC Airfoil Coordinates Database
(e426-il) EPPLER 426 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E426 airfoil Max thickness 10.8% at 25.5% chord Max camber 0.6% at 50.6% chord Source UIUC Airfoil Coordinates Database
(n64108-il) NACA 64-108 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-108 airfoil Max thickness 8% at 40% chord Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database

(n64110-il) NACA 64-110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-110 airfoil Max thickness 10% at 40% chord Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database
(naca641112-il) NACA 64(1)-112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-112 airfoil Max thickness 12% at 40% chord Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database
(s8038-il) S8038 (13%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8038 (13%) low Reynolds number airfoil Max thickness 13% at 32.9% chord Max camber 0.6% at 40.1% chord Source UIUC Airfoil Coordinates Database
(sc20403-il) NASA SC(2)-0403 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0403 airfoil (NASA TP-2969) Max thickness 3% at 36% chord Max camber 0.6% at 85% chord Source UIUC Airfoil Coordinates Database
(sc20406-il) NASA SC(2)-0406 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0406 airfoil (NASA TP-2969) Max thickness 6% at 35% chord Max camber 0.6% at 79% chord Source UIUC Airfoil Coordinates Database