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.

(fx74130wp2mod-il) 74-130 WP2 MOD		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann 74-130 WP2 MOD airfoil Max thickness 12.9% at 43.5% chord Max camber 3.9% at 43.5% chord Max Cl/Cd 110.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe528-il) GOE 528 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 528 airfoil Max thickness 12.5% at 29.8% chord Max camber 6.2% at 39.8% chord Max Cl/Cd 110.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e585-il) EPPLER 585 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E585 sailplane airfoil Max thickness 14.6% at 37.6% chord Max camber 4.2% at 42.8% chord Max Cl/Cd 110.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe610bm-il) GOE 610-B MOD. AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 610-B MOD airfoil Max thickness 7.7% at 30% chord Max camber 5.5% at 40% chord Max Cl/Cd 110.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah7476-il) AH-7-47-6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 7-476 airfoil Max thickness 5.9% at 20% chord Max camber 6.2% at 50% chord Max Cl/Cd 110.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(ah80136-il) AH 80-136		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 80-136 airfoil Max thickness 13.5% at 33.9% chord Max camber 3.4% at 33.9% chord Max Cl/Cd 110.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe426-il) GOE 426 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 426 airfoil Max thickness 13.6% at 30% chord Max camber 4.6% at 40% chord Max Cl/Cd 110.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(clarkv-il) CLARK V AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK V airfoil Max thickness 11.6% at 30% chord Max camber 3.4% at 50% chord Max Cl/Cd 110.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe801-il) GOE 801 (MVA 301) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 801 (MVA 301) airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 110.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe802-il) GOE 802 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 802 airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 110.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database