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 116.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe535-il) GOE 535 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 535 airfoil Max thickness 16.1% at 20% chord Max camber 5.8% at 50% chord Max Cl/Cd 116.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe92-il) GOE 92 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 92 airfoil Max thickness 8.8% at 30% chord Max camber 5.5% at 30% chord Max Cl/Cd 116.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe210-il) GOE 210 (DAIMLER) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 210 (DAIMLER) airfoil Max thickness 6.6% at 30% chord Max camber 4.3% at 40% chord Max Cl/Cd 116.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ah79k132-il) AH 79-K-132/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-K-132/20 airfoil for use with flaps (K) Max thickness 13.2% at 40.2% chord Max camber 3.7% at 40.2% chord Max Cl/Cd 116.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(fx60160-il) FX 60-160 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-160 airfoil Max thickness 15.6% at 40% chord Max camber 3.1% at 60% chord Max Cl/Cd 116.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe326-il) GOE 326 (PFALZ 55) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 326 (Pfalz 55) airfoil Max thickness 8.2% at 29.9% chord Max camber 4.7% at 39.9% chord Max Cl/Cd 116.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e339-il) EPPLER 339 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E339 flying wing airfoil Max thickness 13.5% at 30.1% chord Max camber 4.1% at 25.2% chord Max Cl/Cd 116.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(defcnd1-il) DEFIANT CANARD BL20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan DEFIANT canard BL20 airfoil Max thickness 20.9% at 28.6% chord Max camber 4.5% at 36.1% chord Max Cl/Cd 116.6 at Re# 1,000,000 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 116.5 at Re# 1,000,000 Source NWTC National WInd Technology Center