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.

(bacj-il) BOEING AIRFOIL J (no closed TE)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company airfoil J Max thickness 10.1% at 40% chord Max camber 1.7% at 78% chord Max Cl/Cd 20.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s813-nr) NREL's S813 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S813 tip Max thickness 16% at 40.4% chord Max camber 2.3% at 54.4% chord Max Cl/Cd 20.4 at Re# 50,000 Source NWTC National WInd Technology Center
(s807-nr) NREL's S807 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S807 root Max thickness 18% at 28.7% chord Max camber 1.9% at 78.3% chord Max Cl/Cd 20.3 at Re# 50,000 Source NWTC National WInd Technology Center
(naca633418-il) NACA 63		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63 Max thickness 18% at 33.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 20.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx71120-il) WORTMANN FX 71-120 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-120 airfoil Max thickness 12% at 25% chord Max camber 0% at 0% chord Max Cl/Cd 20.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(mh113-il) MH 113 14.62%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 113 for a propeller for ultralight Max thickness 14.7% at 29.7% chord Max camber 6.4% at 47.7% chord Max Cl/Cd 20.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s1014-il) S1014		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1014 HPV airfoil Max thickness 16.5% at 42.2% chord Max camber 0% at 0% chord Max Cl/Cd 20.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(p51hroot-il) NACA 66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66 Max thickness 15.5% at 45% chord Max camber 1.3% at 47.5% chord Max Cl/Cd 20.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ht12-il) HT12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT12 airfoil Max thickness 5% at 18.6% chord Max camber 0% at 0% chord Max Cl/Cd 20.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe711-il) GOE 711 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 711 airfoil Max thickness 14.9% at 30% chord Max camber 6.3% at 30% chord Max Cl/Cd 20.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database