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.

(goe601-il) GOE 601 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 601 airfoil Max thickness 16% at 39% chord Max camber 2.5% at 49% chord Max Cl/Cd 91.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rc08n1-il) NASA/LANGLEY RC-08(N)1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-08(N)1 rotorcraft airfoil Max thickness 8% at 37.5% chord Max camber 1.6% at 25% chord Max Cl/Cd 91.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s815-nr) NREL's S815 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S815 root 26.0% Dia=20 to 30 m Re=1.2E+6 Clmax(S)=1.46 Clmax(R)=1.40 High max lift coef Max thickness 26.2% at 25.7% chord Max camber 2.9% at 77.9% chord Max Cl/Cd 91.1 at Re# 1,000,000 Source NWTC National WInd Technology Center
(goe346-il) GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 346 (Friedrichshafen-Staaken) airfoil Max thickness 5.7% at 39.9% chord Max camber 3.8% at 39.9% chord Max Cl/Cd 91.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e428-il) EPPLER 428 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E428 airfoil Max thickness 11.1% at 17.2% chord Max camber 0.5% at 50.6% chord Max Cl/Cd 91.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe474-il) GOE 474 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 474 airfoil Max thickness 7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 91 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m22-il) NACA M22 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-22 airfoil Max thickness 6.3% at 30% chord Max camber 6.3% at 30% chord Max Cl/Cd 91 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s6062-il) S6062 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S6062 low Reynolds number airfoil Max thickness 7.9% at 29.4% chord Max camber 1.4% at 43.7% chord Max Cl/Cd 91 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh60-il) MH 60 10.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 60 for flying wings Max thickness 10.1% at 26.9% chord Max camber 1.7% at 36.6% chord Max Cl/Cd 91 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rhodesg36-il) Rhode St. Genese 36		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rhode St. Genese 36 airfoil Max thickness 16.2% at 30% chord Max camber 5.4% at 40% chord Max Cl/Cd 91 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database