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.

(s808-nr) NREL's S808 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S808 root Max thickness 21% at 24.4% chord Max camber 2.4% at 72.9% chord Max Cl/Cd 36.5 at Re# 100,000 Source NWTC National WInd Technology Center
(fx74130wp2-il) 74-130 WP2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann 74-130 WP2 airfoil Max thickness 13% at 43.5% chord Max camber 3.9% at 46.7% chord Max Cl/Cd 36.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rae103-il) RAE 103 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 103 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 36.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(raf27-il) RAF 27 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-27 airfoil Max thickness 9.8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 36.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh94-il) MH 94 16.03%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 94 parafoil Max thickness 16% at 34.1% chord Max camber 1.3% at 74.1% chord Max Cl/Cd 36.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(ste87151-il) EPPLER STE 871-514 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler STE 871-514 airfoil Max thickness 13.9% at 47.3% chord Max camber 2.5% at 79% chord Max Cl/Cd 36.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(davis-corrected-il) DAVIS BASIC B-24 WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Davis basic B-24 wing airfoil Max thickness 15.9% at 29.6% chord Max camber 2.5% at 29.6% chord Max Cl/Cd 36.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e655-il) EPPLER 655 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E655 sailplane airfoil Max thickness 17.3% at 37.3% chord Max camber 3.9% at 42.4% chord Max Cl/Cd 36.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe527-il) GOE 527 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 527 airfoil Max thickness 16.5% at 29.5% chord Max camber 5.8% at 39.5% chord Max Cl/Cd 36.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e694-il) EPPLER 694 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E694 sailplane airfoil Max thickness 15.4% at 40.4% chord Max camber 4.9% at 59.2% chord Max Cl/Cd 36.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database