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.

(goe421-il) GOE 421 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 421 airfoil Max thickness 19% at 29.3% chord Max camber 8.1% at 49.3% chord Max Cl/Cd 76.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh92-il) MH 92 15.49%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 92 parafoil Max thickness 15.5% at 27.4% chord Max camber 1.4% at 15.1% chord Max Cl/Cd 76.6 at Re# 500,000 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 76.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe386-il) GOE 386 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 386 airfoil Max thickness 20.3% at 29% chord Max camber 5.4% at 39% chord Max Cl/Cd 76.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(pw51-pw) PW51		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Airfoil for plank model gliders Max thickness 8.9% at 27.5% chord Max camber 1.4% at 27.5% chord Max Cl/Cd 76.6 at Re# 500,000 Source RC Groups

(s808-nr) NREL's S808 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S808 root Max thickness 21% at 24.4% chord Max camber 2.4% at 72.9% chord Max Cl/Cd 76.6 at Re# 500,000 Source NWTC National WInd Technology Center
(goe548-il) GOE 548 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 548 airfoil Max thickness 11.9% at 40% chord Max camber 2.3% at 50% chord Max Cl/Cd 76.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx77w270-il) FX 77-W-270		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-W-270 airfoil for use on wind turbines (W) Max thickness 27.1% at 33.9% chord Max camber 4.3% at 27.9% chord Max Cl/Cd 76.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e625-il) EPPLER 625 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E625 airfoil Max thickness 13% at 30% chord Max camber 2.9% at 22.5% chord Max Cl/Cd 76.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(tsagi12-il) TSAGI 12% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TSAGI 12% airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 76.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database