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.

(fx2-il) WORTMANN FX 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 2 airfoil Max thickness 20.4% at 43.5% chord Max camber 3.8% at 69.1% chord Max Cl/Cd 18 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ea81006-il) EPPLER EA 8(-1)-006 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 8(-1)-006 airfoil Max thickness 6% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 17.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e543-il) EPPLER 543 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E543 general aviation airfoil Max thickness 17.2% at 40.7% chord Max camber 1.9% at 31% chord Max Cl/Cd 17.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe243-il) GOE 243 (MVA PR.3) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 243 (MVA PR.3) airfoil Max thickness 19% at 29.3% chord Max camber 8.4% at 59.4% chord Max Cl/Cd 17.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(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 17.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe801-il) GOE 801 (MVA 301) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 801 (MVA 301) airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 17.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe802-il) GOE 802 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 802 airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 17.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s817-nr) NREL's S817 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S817 tip 16.0% Dia=30 to 50 m Re=3.0E+6 Clmax(S)=1.10 Clmax(R)=1.08 Restrained max lift coef Max thickness 16% at 51.1% chord Max camber 2.8% at 41.1% chord Max Cl/Cd 17.9 at Re# 50,000 Source NWTC National WInd Technology Center
(e553-il) EPPLER 553 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E553 general aviation airfoil Max thickness 18.1% at 31.8% chord Max camber 2.9% at 56.6% chord Max Cl/Cd 17.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ui1720-il) UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Illinois UI-1720 high lift airfoil Max thickness 13.8% at 19% chord Max camber 4.6% at 21.2% chord Max Cl/Cd 17.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database