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.

(eiffel428-il) Eiffel 428 (Bleriot)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 428 (Bleriot) airfoil Max thickness 9% at 30% chord Max camber 4.2% at 40% chord Max Cl/Cd 59.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s1210-il) S1210 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1210 high lift low Reynolds number airfoil Max thickness 12% at 21.4% chord Max camber 6.7% at 51.1% chord Max Cl/Cd 59.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe225-il) GOE 225 (MVA H.35) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 225 (MVA H.35) airfoil Max thickness 12.8% at 19.7% chord Max camber 7.6% at 49.7% chord Max Cl/Cd 59.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe392-il) GOE 392 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 392 airfoil Max thickness 10.2% at 30% chord Max camber 4.8% at 40% chord Max Cl/Cd 59.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe403-il) GOE 403 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 403 airfoil Max thickness 6.7% at 29.9% chord Max camber 4.3% at 39.9% chord Max Cl/Cd 59.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(kc135winglet-il) KC-135 Winglet (supercritical Whitcomb)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 winglet airfoil designed by Richard T. Whitcomb Max thickness 8% at 40% chord Max camber 2.7% at 65% chord Max Cl/Cd 59.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe57-il) GOE 57 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 57 airfoil Max thickness 6.3% at 19.9% chord Max camber 5.1% at 39.9% chord Max Cl/Cd 59.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sd7043-il) SD7043 (9.1%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7043 low Reynolds number airfoil Max thickness 9.1% at 26.6% chord Max camber 3.3% at 50.2% chord Max Cl/Cd 59.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe369-il) GOE 369 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 369 airfoil Max thickness 5.9% at 30% chord Max camber 5.4% at 40% chord Max Cl/Cd 59.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(be50sm-il) BE50 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 23.8% chord Max camber 4% at 45.4% chord Max Cl/Cd 59.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database