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.

(goe652-il) GOE 652 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 652 airfoil Max thickness 17.1% at 20% chord Max camber 9.3% at 50% chord Max Cl/Cd 77.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe428-il) GOE 428 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 428 airfoil Max thickness 7.9% at 30% chord Max camber 5.2% at 40% chord Max Cl/Cd 77.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s7055-il) S7055 (10.5%) Flat-Bottomed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S7055 low Reynolds number airfoil Max thickness 10.5% at 31.8% chord Max camber 3.3% at 38.6% chord Max Cl/Cd 77.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sd2030-il) SD2030-086-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD2030 low Reynolds number airfoil Max thickness 8.6% at 35.5% chord Max camber 2.2% at 45.3% chord Max Cl/Cd 77.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n63412-il) NACA 63-412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(1)-412 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 77.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(e178-il) E178 (8.69%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E178 low Reynolds number airfoil Max thickness 8.7% at 29.8% chord Max camber 2.8% at 38.8% chord Max Cl/Cd 77.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe515-il) GOE 515 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 515 airfoil Max thickness 8.5% at 30% chord Max camber 2.8% at 40% chord Max Cl/Cd 77.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e591-il) E591		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E591 airfoil Max thickness 15.7% at 25% chord Max camber 6% at 52.3% chord Max Cl/Cd 77.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e668-il) EPPLER 668 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E668 sailplane airfoil Max thickness 13.9% at 37.3% chord Max camber 4% at 47.8% chord Max Cl/Cd 77.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe591-il) GOE 591 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 591 airfoil Max thickness 11.2% at 30% chord Max camber 5.1% at 40% chord Max Cl/Cd 77.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database