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.

(mh106-il) MH 106 13.07%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 106 for stall controlled wind turbines Max thickness 13.1% at 27.4% chord Max camber 0.9% at 27.4% chord Max Cl/Cd 61.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh60-il) MH 60 10.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 60 for flying wings Max thickness 10.1% at 26.9% chord Max camber 1.7% at 36.6% chord Max Cl/Cd 61.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e546-il) EPPLER 546 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E546 general aviation airfoil Max thickness 16.2% at 40.3% chord Max camber 1.8% at 26.2% chord Max Cl/Cd 61.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag12-il) AG12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG12 airfoil Max thickness 6.2% at 20.8% chord Max camber 1.8% at 42.8% chord Max Cl/Cd 61.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe416a-il) GOE 416A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 416A airfoil Max thickness 11.7% at 29.5% chord Max camber 1.3% at 59.6% chord Max Cl/Cd 61.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(pw106-pw) PW106		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Modified PW51 with higher camber and therefore a higher clmax Max thickness 8.9% at 27.5% chord Max camber 2.1% at 27.5% chord Max Cl/Cd 61.3 at Re# 200,000 Source RC Groups
(sc21006-il) NASA SC(2)-1006 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-1006 airfoil Max thickness 6% at 30% chord Max camber 2.6% at 73% chord Max Cl/Cd 61.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(miley-il) MILEY M06-13-128		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Miley MO6-13-128 airfoil Max thickness 12.9% at 35% chord Max camber 4.9% at 35% chord Max Cl/Cd 61.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e546-il) EPPLER 546 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E546 general aviation airfoil Max thickness 16.2% at 40.3% chord Max camber 1.8% at 26.2% chord Max Cl/Cd 61.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca4421-il) NACA 4421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4421 airfoil Max thickness 21% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 61.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database