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.

(sc20614-il) NASA SC(2)-0614 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0614 airfoil (NASA TP-2969) Max thickness 14% at 36% chord Max camber 2.1% at 81% chord Max Cl/Cd 26.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe06k-il) GOE 6K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 6K airfoil Max thickness 7.5% at 50% chord Max camber 3.1% at 50% chord Max Cl/Cd 26.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ls013-il) NASA/LANGLEY LS(1)-0013 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0013 general aviation airfoil Max thickness 12.9% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 26.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sg6040-il) SG6040		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6040 wind turbine airfoil Max thickness 16% at 35.3% chord Max camber 2.3% at 60.5% chord Max Cl/Cd 26.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n63010a-il) NACA 63A010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-010A airfoil Max thickness 10% at 35% chord Max camber 0% at 0% chord Max Cl/Cd 26.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(naca0018-il) NACA 0018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0018 airfoil Max thickness 18% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 26.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe549-il) GOE 549 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 549 airfoil Max thickness 13.9% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 26.4 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 26.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ebambino7-il) E. Bambino		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	E. Bambino airfoil Max thickness 6% at 40% chord Max camber 1.9% at 20% chord Max Cl/Cd 26.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ls417mod-il) NASA/LANGLEY LS(1)-0417MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0417MOD general aviation airfoil Max thickness 17% at 30.2% chord Max camber 2.3% at 20.2% chord Max Cl/Cd 26.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database