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.

(goe385-il) GOE 385 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 385 airfoil Max thickness 9.9% at 29.9% chord Max camber 4.1% at 29.9% chord Max Cl/Cd 73 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hq259-il) HQ 2.5/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 2.5% at 50% chord Max Cl/Cd 73 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sa7036-il) SA7036		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7036 Max thickness 9.2% at 28.1% chord Max camber 2.6% at 42.1% chord Max Cl/Cd 73 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx61168-il) FX 61-168 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-168 airfoil Max thickness 16.8% at 37.1% chord Max camber 3% at 37.1% chord Max Cl/Cd 73 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hor07-il) ONERA HOR07 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 7.2% at 23.2% chord Max camber 4.5% at 39.6% chord Max Cl/Cd 73 at Re# 200,000 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 73 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa22-il) USA 22 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-22 airfoil Max thickness 9.1% at 19.9% chord Max camber 4.4% at 39.9% chord Max Cl/Cd 73 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe223-il) GOE 223 (MVA H.34) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 223 (MVA H.34) airfoil Max thickness 18.8% at 29.1% chord Max camber 5.7% at 49.1% chord Max Cl/Cd 73 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe414-il) GOE 414 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 414 airfoil Max thickness 13.6% at 29.7% chord Max camber 5.3% at 39.7% chord Max Cl/Cd 73 at Re# 200,000 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 72.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database