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.

(goe621-il) GOE 621 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 621 airfoil Max thickness 15% at 29.5% chord Max camber 5% at 49.5% chord Max Cl/Cd 27.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe298-il) GOE 298 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 298 airfoil Max thickness 12.8% at 19.6% chord Max camber 4.5% at 39.6% chord Max Cl/Cd 27.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe365-il) GOE 365 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 365 airfoil Max thickness 11.7% at 29.9% chord Max camber 5.1% at 39.9% chord Max Cl/Cd 27.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ames03-il) NASA/AMES A-03 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Kennelly A-03 transonic rotorcraft airfoil Max thickness 10% at 37.5% chord Max camber 1.2% at 17.5% chord Max Cl/Cd 27.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx69h098-il) BELL/WORTMANN FX 69-H-098 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell/Wortmann FX 69-H-098 rotorcraft airfoil Max thickness 9.9% at 28.2% chord Max camber 1.7% at 22.5% chord Max Cl/Cd 27.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(s8035-il) S8035 for RC aerobatic 14% thick		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8035 low Reynolds number airfoil Max thickness 14% at 29.1% chord Max camber 0% at 0% chord Max Cl/Cd 27.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e662-il) EPPLER E662 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E662 sailplane airfoil Max thickness 15% at 42.8% chord Max camber 4.1% at 47.5% chord Max Cl/Cd 27.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe550-il) GOE 550 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 550 airfoil Max thickness 13% at 20% chord Max camber 4.3% at 50% chord Max Cl/Cd 27.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e329-il) EPPLER 329 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E329 flying wing airfoil Max thickness 13.5% at 30.6% chord Max camber 3.5% at 25.7% chord Max Cl/Cd 27.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n64108-il) NACA 64-108 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-108 airfoil Max thickness 8% at 40% chord Max camber 0.6% at 50% chord Max Cl/Cd 27.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database