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.

(fx60100-il) FX 60-100 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-100 airfoil Max thickness 10% at 27.9% chord Max camber 3.6% at 56.5% chord Max Cl/Cd 87.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n2414-il) NACA 2414		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2414 airfoil Max thickness 14% at 29.5% chord Max camber 2% at 39.6% chord Max Cl/Cd 87.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx66h80-il) FX 66-H-80		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-H-80 airfoil Max thickness 8% at 27.9% chord Max camber 2.5% at 25% chord Max Cl/Cd 87.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca65410-il) NACA 65-410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-410 airfoil Max thickness 10% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 87.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe289-il) GOE 289 (MVA 289) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 289 (MVA 289) airfoil Max thickness 16.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 87.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(m6-il) NACA M6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-6 airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 87.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe54-il) GOE 54 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 54 airfoil Max thickness 6.5% at 14.9% chord Max camber 3.5% at 19.9% chord Max Cl/Cd 87.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s812-nr) NREL's S812 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S812 primary Max thickness 21% at 39.6% chord Max camber 1.6% at 77% chord Max Cl/Cd 87.4 at Re# 500,000 Source NWTC National WInd Technology Center
(e546-il) EPPLER 546 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E546 general aviation airfoil Max thickness 16.2% at 40.3% chord Max camber 1.8% at 26.2% chord Max Cl/Cd 87.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe738-il) GOE 738 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 738 airfoil Max thickness 15.4% at 30% chord Max camber 2.1% at 30% chord Max Cl/Cd 87.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database