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.

(naca16021-il) NACA 16-021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-021 airfoil Max thickness 21% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 20.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ah93w480b-il) AH 93-W-480B		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-480B airfoil for use on wind turbines (W) Max thickness 47.8% at 44.1% chord Max camber 3.6% at 44.1% chord Max Cl/Cd 20.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(dsma523a-il) DSMA-523A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	McDonnell/Douglas DSMA-523 transonic airfoil with sharp trailing edge Max thickness 11% at 36% chord Max camber 2.3% at 82% chord Max Cl/Cd 20.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe798-il) GOE 798 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 798 airfoil Max thickness 20% at 30% chord Max camber 6% at 40% chord Max Cl/Cd 20.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca654421-il) NACA 65(4)-421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-421 airfoil Max thickness 21% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 20.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(naca16006-il) NACA 16-006		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-006 airfoil Max thickness 6% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 20.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(r1046-il) RONCZ 1046 VOYAGER CANARD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1046 Voyager canard airfoil Max thickness 18.1% at 38% chord Max camber 6.7% at 42% chord Max Cl/Cd 20.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s827-nr) NREL's S827 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S827 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.00 Clmax(R)=0.99 Restrained max lift coef Max thickness 21% at 44.9% chord Max camber 2.2% at 68% chord Max Cl/Cd 20.4 at Re# 100,000 Source NWTC National WInd Technology Center
(fx08s176-il) WORTMANN FX 08-S-176 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 08-S-176 airfoil Max thickness 17.6% at 37.1% chord Max camber 5.7% at 37.1% chord Max Cl/Cd 20.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe443-il) GOE 443 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 443 airfoil Max thickness 5% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 20.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database