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.

(goe534-il) GOE 534 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 534 airfoil Max thickness 14.1% at 19.6% chord Max camber 5.2% at 39.6% chord Max Cl/Cd 91 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s2060-il) S2060 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2060 low Reynolds number airfoil Max thickness 8% at 30.2% chord Max camber 1.6% at 49.7% chord Max Cl/Cd 91 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e545-il) EPPLER 545 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E545 general aviation airfoil Max thickness 17.4% at 39.3% chord Max camber 1.8% at 29.9% chord Max Cl/Cd 91 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe802b-il) GOE 802 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 802 B airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 91 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mue139-il) MUE 139		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	MUE 139 airfoil Max thickness 13.9% at 22.2% chord Max camber 4.7% at 30.9% chord Max Cl/Cd 90.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(df101-il) DF 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	David Fraser DF 101 low Reynolds number airfoil Max thickness 11% at 29.1% chord Max camber 2.3% at 43.5% chord Max Cl/Cd 90.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(clarky-il) CLARK Y AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK Y airfoil Max thickness 11.7% at 28% chord Max camber 3.4% at 42% chord Max Cl/Cd 90.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe415-il) GOE 415 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 415 airfoil Max thickness 8.5% at 19.9% chord Max camber 3.7% at 29.9% chord Max Cl/Cd 90.9 at Re# 500,000 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 90.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah79k143-il) AH 79-K-143/18		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-K-143/18 airfoil for use with flaps (K) Max thickness 14.3% at 40.2% chord Max camber 2.9% at 40.2% chord Max Cl/Cd 90.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database