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.

(waspsm-il) WASP (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Mike Fox WASP low Reynolds number airfoil Max thickness 9.4% at 27.1% chord Max camber 3% at 37.9% chord Max Cl/Cd 51 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag36-il) AG36		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG36 airfoil Max thickness 8.2% at 27.9% chord Max camber 2.3% at 37% chord Max Cl/Cd 51 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe482-il) GOE 482 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 482 airfoil Max thickness 16.5% at 29.6% chord Max camber 8.8% at 39.6% chord Max Cl/Cd 51 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh200-il) MH 200 12.97%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 200 for a canard airplane (main wing) Max thickness 13% at 39.5% chord Max camber 2.1% at 49.8% chord Max Cl/Cd 51 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe563-il) GOE 563 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 563 airfoil Max thickness 8.9% at 29.8% chord Max camber 2.2% at 49.8% chord Max Cl/Cd 51 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(e397-il) EPPLER 397 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E397 human powered aircraft airfoil Max thickness 13.5% at 29.4% chord Max camber 5.3% at 52.1% chord Max Cl/Cd 51 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e49-il) EPPLER 49 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E49 low Reynolds number airfoil Max thickness 7.2% at 38.4% chord Max camber 6.5% at 62.2% chord Max Cl/Cd 50.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s805a-nr) NREL's S805A Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S805A primary Max thickness 13.5% at 40% chord Max camber 2.1% at 35% chord Max Cl/Cd 50.9 at Re# 100,000 Source NWTC National WInd Technology Center
(goe100-il) GOE 100 (SOPWITH) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 100 (Sopwith) airfoil Max thickness 6.6% at 20% chord Max camber 3.6% at 39.9% chord Max Cl/Cd 50.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sg6040-il) SG6040		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6040 wind turbine airfoil Max thickness 16% at 35.3% chord Max camber 2.3% at 60.5% chord Max Cl/Cd 50.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database