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.

(goe411-il) GOE 411 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 411 airfoil Max thickness 13.2% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 45.8 at Re# 500,000 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 45.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca001234-il) NACA 0012-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-34 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 45.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(cp-060-050-gn) Cambered plate C=6% T=5% R=2.11		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=6% Wall thickness=5% Radius=2.113 Max thickness 10.8% at 6.3% chord Max camber 2.7% at 52.1% chord Max Cl/Cd 45.2 at Re# 500,000 Source Generated
(fx77w343-il) WORTMANN FX 77-W-343 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-W-343 wind turbine airfoil Max thickness 34.4% at 33.9% chord Max camber 4.7% at 25% chord Max Cl/Cd 45.2 at Re# 500,000 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 45.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(cp-080-050-gn) Cambered plate C=8% T=5% R=1.6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=8% Wall thickness=5% Radius=1.603 Max thickness 8.4% at 5% chord Max camber 5.3% at 47% chord Max Cl/Cd 44.8 at Re# 500,000 Source Generated
(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 44.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx3-il) WORTMANN FX 3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 3 airfoil Max thickness 20% at 50% chord Max camber 4.2% at 75% chord Max Cl/Cd 44.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca16015-il) NACA 16-015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-015 airfoil Max thickness 15% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 44.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database