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.

(goe190-il) GOE 190 (MVA MK.18) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 190 (MVA MK.18) airfoil Max thickness 12.7% at 19.7% chord Max camber 5.9% at 49.7% chord Max Cl/Cd 52.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(du84132v-il) DELFT DU84-132V3 AIRFOIL (MEASURED)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Airfoil measured from an ASW22 wing Max thickness 13.6% at 33.9% chord Max camber 3.1% at 45.3% chord Max Cl/Cd 52.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(raf6-il) RAF 6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-6 airfoil Max thickness 10% at 30% chord Max camber 4.6% at 30% chord Max Cl/Cd 52.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe685-il) GOE 685 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 685 airfoil Max thickness 13.1% at 19.6% chord Max camber 4.2% at 49.5% chord Max Cl/Cd 52.5 at Re# 100,000 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 52.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(eiffel385-il) Eiffel 385 (S.T. Ae)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 385 (S.T. Ae) airfoil Max thickness 13.4% at 20% chord Max camber 4.4% at 50% chord Max Cl/Cd 52.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe364-il) GOE 364 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 364 airfoil Max thickness 10.8% at 30% chord Max camber 6.5% at 30% chord Max Cl/Cd 52.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sg6050-il) SG6050		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6050 wind turbine airfoil Max thickness 16% at 31.5% chord Max camber 3.1% at 48.9% chord Max Cl/Cd 52.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hq2012-il) HQ 2.0/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2% at 50% chord Max Cl/Cd 52.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe619-il) GOE 619 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 619 airfoil Max thickness 13.7% at 19.5% chord Max camber 4.5% at 49.5% chord Max Cl/Cd 52.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database