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.

(e748-il) EPPLER 748 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E748 sailplane airfoil Max thickness 19.7% at 27.4% chord Max camber 4.6% at 54.9% chord Max Cl/Cd 94.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e220-il) E220 (11.48%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E220 low Reynolds number airfoil Max thickness 11.5% at 33.1% chord Max camber 2.2% at 37.7% chord Max Cl/Cd 94.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe479-il) GOE 479 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 479 airfoil Max thickness 11.6% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 94.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah93156-il) AH 93-156		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-156 airfoil Max thickness 15.7% at 39.5% chord Max camber 3.7% at 41.5% chord Max Cl/Cd 94.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s7012-il) S7012 8.75%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S7012 low Reynolds number airfoil Max thickness 8.7% at 27.7% chord Max camber 1.7% at 38.1% chord Max Cl/Cd 94.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(mh83-il) MH 83 13.29%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 83 for flying wings (hang glider) Max thickness 13.3% at 20.6% chord Max camber 4.5% at 32.6% chord Max Cl/Cd 94.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe633-il) GOE 633 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 633 airfoil Max thickness 13.8% at 19.7% chord Max camber 4% at 39.7% chord Max Cl/Cd 94.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe331-il) GOE 331 (PFALZ 60) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 331 (Pfalz 60) airfoil Max thickness 10.6% at 29.9% chord Max camber 6.9% at 39.9% chord Max Cl/Cd 94.1 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 94 at Re# 500,000 Source NWTC National WInd Technology Center
(s825-nr) NREL's S825 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S825 primary 17.0% Dia=20 to 40 m Re=2.0E+6 Clmax(S)=1.44 Clmax(R)=1.37 High max lift coef Max thickness 17.1% at 29.9% chord Max camber 3.9% at 65.3% chord Max Cl/Cd 94 at Re# 500,000 Source NWTC National WInd Technology Center