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.

(goe549-il) GOE 549 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 549 airfoil Max thickness 13.9% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 74.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe476-il) GOE 476 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 476 airfoil Max thickness 14.5% at 29.5% chord Max camber 5.2% at 39.5% chord Max Cl/Cd 74.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(be50sm-il) BE50 (smoothed)		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 23.8% chord Max camber 4% at 45.4% chord Max Cl/Cd 74.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe06k-il) GOE 6K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 6K airfoil Max thickness 7.5% at 50% chord Max camber 3.1% at 50% chord Max Cl/Cd 74.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(clarkysm-il) CLARK-Y 11.7% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK Y airfoil (smoothed) Max thickness 11.7% at 30.9% chord Max camber 3.5% at 43.5% chord Max Cl/Cd 74.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe187-il) GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 187 (Schatte-Lanz 2U10) airfoil Max thickness 8.3% at 30% chord Max camber 4.8% at 30% chord Max Cl/Cd 74.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah93k131-il) AH 93-K-131/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-131/15 airfoil for use with flaps (K) Max thickness 13.1% at 41.3% chord Max camber 3.6% at 41.3% chord Max Cl/Cd 74.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(eiffel385-il) Eiffel 385 (S.T. Ae)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 385 (S.T. Ae) airfoil Max thickness 13.4% at 20% chord Max camber 4.4% at 50% chord Max Cl/Cd 74.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(l7769-il) LISSAMAN 7769 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lissaman 7769 human powered aircraft airfoil Max thickness 11% at 30% chord Max camber 4.4% at 30% chord Max Cl/Cd 74.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usnps4-il) USNPS4 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Jacobs USNPS4 (smoothed) 17.5 kW wind turbine airfoil Max thickness 11.9% at 34.2% chord Max camber 5% at 34.2% chord Max Cl/Cd 74.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database