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.

(usa40-il) USA 40 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-40 airfoil Max thickness 13.3% at 30% chord Max camber 4.2% at 40% chord Max Cl/Cd 95.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(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 Max Cl/Cd 95.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(usa27-il) USA 27 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-27 airfoil Max thickness 11.1% at 30% chord Max camber 5.1% at 40% chord Max Cl/Cd 95.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe478-il) GOE 478 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 478 airfoil Max thickness 13.4% at 29.6% chord Max camber 4.3% at 39.6% chord Max Cl/Cd 95.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(be50-il) BE50 (original)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 25% chord Max camber 4.1% at 45% chord Max Cl/Cd 95.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(n10-il) N-10		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-10 airfoil Max thickness 11.2% at 30% chord Max camber 3.6% at 40% chord Max Cl/Cd 95.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe281-il) GOE 281 (DAIMLER XII) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 281 (DAIMLER XII) airfoil Max thickness 8% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 95.3 at Re# 500,000 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 Max Cl/Cd 95.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(la2573a-il) LA2573A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Liebeck LA2573A airfoil Max thickness 13.7% at 28.8% chord Max camber 3.2% at 26.1% chord Max Cl/Cd 95.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s830-nr) NREL's S830 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S830 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.60 Clmax(R)=1.57 High max lift coef Max thickness 21% at 38.4% chord Max camber 4.4% at 70.5% chord Max Cl/Cd 95.2 at Re# 500,000 Source NWTC National WInd Technology Center