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.

(oaf095-il) OAF095 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF095 Fenestron airfoil Max thickness 9.5% at 23.2% chord Max camber 3.9% at 53.1% chord Max Cl/Cd 43.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(oaf095-il) OAF095 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF095 Fenestron airfoil Max thickness 9.5% at 23.2% chord Max camber 3.9% at 53.1% chord Max Cl/Cd 43.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe210-il) GOE 210 (DAIMLER) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 210 (DAIMLER) airfoil Max thickness 6.6% at 30% chord Max camber 4.3% at 40% chord Max Cl/Cd 43.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe164-il) GOE 164 (MVA MK.10) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 164 (MVA MK.10) airfoil Max thickness 8.9% at 19.9% chord Max camber 6.6% at 39.9% chord Max Cl/Cd 43.8 at Re# 50,000 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 43.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe804-il) GOE 804 (EA 8) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 804 (EA 8) airfoil Max thickness 6% at 40% chord Max camber 6.3% at 50% chord Max Cl/Cd 43.7 at Re# 50,000 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 43.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ma409sm-il) MA409 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Michael Achterberg MA409 F1C class free flight airfoil (smoothed) Max thickness 6.7% at 23.8% chord Max camber 3.3% at 49.3% chord Max Cl/Cd 43.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe240-il) GOE 240 (KOLLER) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 240 (KOLLER) airfoil Max thickness 7% at 29.9% chord Max camber 5.2% at 39.9% chord Max Cl/Cd 43.5 at Re# 50,000 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 43.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database