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.

(e209-il) E209 (13.72%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E209 low Reynolds number airfoil Max thickness 13.7% at 33.8% chord Max camber 1.6% at 48.1% chord Max Cl/Cd 93 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe741-il) GOE 741 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 741 airfoil Max thickness 15.3% at 30% chord Max camber 4.8% at 30% chord Max Cl/Cd 93 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe442-il) GOE 442 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 442 airfoil Max thickness 7.7% at 19.9% chord Max camber 4.3% at 39.9% chord Max Cl/Cd 93 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s9000-il) S9000 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9000 (9%) low Reynolds number airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 28.2% chord Max camber 2.1% at 44.8% chord Max Cl/Cd 93 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hobie-il) HOBIE		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hobie Hawk airfoil (Hobie Hawk R/C sailplane) Max thickness 8.5% at 25% chord Max camber 4% at 45% chord Max Cl/Cd 93 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe133-il) GOE 133 (MVA H.11) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 133 (MVA H.11) airfoil Max thickness 7.9% at 30% chord Max camber 4.3% at 30% chord Max Cl/Cd 93 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe372-il) GOE 372 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 372 airfoil Max thickness 6.2% at 29.9% chord Max camber 4.3% at 39.9% chord Max Cl/Cd 93 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe279-il) GOE 279 (DAIMLER X) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 279 (DAIMLER X) airfoil Max thickness 7.4% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 93 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(usa26-il) USA 26 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-26 airfoil Max thickness 9.8% at 19.9% chord Max camber 4.3% at 39.9% chord Max Cl/Cd 92.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ls417-il) NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Whitcomb LS(1)-0417 (GA(W)-1) general aviation airfoil Max thickness 17% at 40% chord Max camber 2.4% at 65% chord Max Cl/Cd 92.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database