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.

(august160-il) AUGUST 160		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AUGUST 160 airfoil Max thickness 16% at 25% chord Max camber 5.4% at 25% chord Max Cl/Cd 90.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe243-il) GOE 243 (MVA PR.3) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 243 (MVA PR.3) airfoil Max thickness 19% at 29.3% chord Max camber 8.4% at 59.4% chord Max Cl/Cd 90.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe418-il) GOE 418 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 418 airfoil Max thickness 12.7% at 20% chord Max camber 5.1% at 40% chord Max Cl/Cd 90.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe675-il) GOE 675 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 675 airfoil Max thickness 14.9% at 29.5% chord Max camber 5.9% at 39.5% chord Max Cl/Cd 90.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(clarkysm-il) CLARK-Y 11.7% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK Y airfoil (smoothed) Max thickness 11.7% at 30.9% chord Max camber 3.5% at 43.5% chord Max Cl/Cd 90.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(e547-il) EPPLER 547 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E547 general aviation airfoil Max thickness 17.4% at 40.3% chord Max camber 2% at 30.7% chord Max Cl/Cd 90.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fg2-il) Fage & Collins 2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fage & Collins 2 airfoil Max thickness 8.2% at 30% chord Max camber 3.3% at 30% chord Max Cl/Cd 90.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx69h083-il) BELL/WORTMANN FX 69-H-083 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-083 rotorcraft airfoil Max thickness 8.4% at 33.3% chord Max camber 2.5% at 33.3% chord Max Cl/Cd 90.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sd7037-il) SD7037-092-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7037 low Reynolds number airfoil Max thickness 9.2% at 26.1% chord Max camber 2.5% at 44.7% chord Max Cl/Cd 90.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(usa45-il) USA 45 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-45 airfoil Max thickness 14.5% at 29.8% chord Max camber 4.1% at 29.8% chord Max Cl/Cd 90 at Re# 500,000 Source UIUC Airfoil Coordinates Database