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.

(goe198-il) GOE 198 (L.F.G. 5294) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 198 (L.F.G. 5294) airfoil Max thickness 7.8% at 19.9% chord Max camber 6.5% at 39.9% chord Max Cl/Cd 64 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e64-il) E64 (8.45%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E64 low Reynolds number airfoil Max thickness 8.4% at 27.8% chord Max camber 2.9% at 56.5% chord Max Cl/Cd 64 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(psu94097-il) PSU 94-097 (AIAA 2001-2478)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Maughmer PSU 94-097 winglet airfoil Max thickness 9.7% at 32.3% chord Max camber 4% at 46.3% chord Max Cl/Cd 64 at Re# 100,000 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 63.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx63137-il) WORTMANN FX 63-137 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-137 human power aircraft airfoil (Liver Puffin) airfoil Max thickness 13.7% at 30.9% chord Max camber 6% at 53.3% chord Max Cl/Cd 63.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe124-il) GOE 124 (MVA H.4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 124 (MVA H.4) airfoil Max thickness 7.9% at 29.9% chord Max camber 5.6% at 39.9% chord Max Cl/Cd 63.9 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 63.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e377m-il) EPPLER 377 (MODIFIED) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E377 (modified) ultralight airfoil Max thickness 3.8% at 6.1% chord Max camber 9.2% at 32.6% chord Max Cl/Cd 63.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n6409-il) NACA6409 9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6409 Max thickness 9% at 29.3% chord Max camber 6% at 39.6% chord Max Cl/Cd 63.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e66-il) EPPLER 66 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E66 low Reynolds number airfoil Max thickness 10.1% at 28.7% chord Max camber 4.1% at 52.3% chord Max Cl/Cd 63.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database