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.

(naca16021-il) NACA 16-021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-021 airfoil Max thickness 21% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 39.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(bambino6-il) Bambino 6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bambino 6 airfoil Max thickness 12% at 40% chord Max camber 2.8% at 40% chord Max Cl/Cd 39.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(eiffel10-il) Eiffel 10 (Wright) - 1903 Wright Flyer airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 10 (Wright) - 1903 Wright Flyer airfoil Max thickness 2.7% at 0% chord Max camber 6.1% at 40% chord Max Cl/Cd 38.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(m1-il) NACA-M1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-1 airfoil Max thickness 6.2% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 38.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe445-il) GOE 445 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 445 airfoil Max thickness 6.4% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 38 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(naca16009-il) NACA 16009		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16009 airfoil Max thickness 9% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 38 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e864-il) EPPLER 864 STRUT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E864 strut airfoil Max thickness 38.8% at 32.7% chord Max camber 0.1% at 10.8% chord Max Cl/Cd 37.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(r140-il) R140 (original)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	R140 Quickee 500 airfoil (original) Max thickness 12% at 39.3% chord Max camber 0.5% at 42.3% chord Max Cl/Cd 37.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca000834-il) NACA 0008-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 37.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe451-il) GOE 451 AIRFOIL (modified line 6)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 451 airfoil Max thickness 4.4% at 30% chord Max camber 5.6% at 40% chord Max Cl/Cd 37.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database