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.

(e550-il) EPPLER 550 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E550 general aviation airfoil Max thickness 18.2% at 34% chord Max camber 2.2% at 29.4% chord Max Cl/Cd 33.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca0012h-sa) NACA0012H for VAWT from Sandia report SAND80-2114		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Modified Naca 0012 airfoil for Sandia VAWT tests Max thickness 12.2% at 22.5% chord Max camber 0% at 0% chord Max Cl/Cd 33.5 at Re# 100,000 Source Sandia National Laboratories
(naca662415-il) NACA 66(2)-415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(2)-415 airfoil Max thickness 15% at 45% chord Max camber 2.2% at 50% chord Max Cl/Cd 33.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ea61012-il) EPPLER EA 6(-1)-012 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 6(-1)-012 airfoil Max thickness 12% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 33.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca0010-il) NACA 0010		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 33.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(ah82150f-il) AH 82-150 F		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 82-150 F airfoil Max thickness 15% at 43.5% chord Max camber 3.6% at 46.7% chord Max Cl/Cd 33.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca4424-il) NACA 4424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4424 airfoil Max thickness 24% at 29.4% chord Max camber 4% at 40% chord Max Cl/Cd 33.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n0009sm-il) NACA-0009 9.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0009 airfoil (smoothed) Max thickness 9% at 30.9% chord Max camber 0% at 0% chord Max Cl/Cd 33.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e426-il) EPPLER 426 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E426 airfoil Max thickness 10.8% at 25.5% chord Max camber 0.6% at 50.6% chord Max Cl/Cd 33.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sc20712-il) NASA SC(2)-0712 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0712 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 2.2% at 81% chord Max Cl/Cd 33.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database