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.

(rg14-il) RG 14 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 14 airfoil Max thickness 8.5% at 29.7% chord Max camber 1.6% at 39.2% chord Max Cl/Cd 84.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rg149-il) RG 14 9% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 14 (9%) airfoil Max thickness 9% at 31% chord Max camber 1.6% at 36% chord Max Cl/Cd 84.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s819-nr) NREL's S819 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S819 primary 21.0% Dia=10 to 20 m Re=1.0E+6 Clmax(S)=1.20 Clmax(R)=1.16 Restrained max lift coef Max thickness 21.1% at 28.4% chord Max camber 1.3% at 77.3% chord Max Cl/Cd 84.1 at Re# 1,000,000 Source NWTC National WInd Technology Center
(goe514-il) GOE 514 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 514 airfoil Max thickness 16.6% at 19.7% chord Max camber 6.4% at 39.7% chord Max Cl/Cd 84.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx66h60-il) FX 66-H-60		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-H-60 airfoil Max thickness 6% at 22.2% chord Max camber 1.7% at 17% chord Max Cl/Cd 84.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(eiffel428-il) Eiffel 428 (Bleriot)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 428 (Bleriot) airfoil Max thickness 9% at 30% chord Max camber 4.2% at 40% chord Max Cl/Cd 84 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e360-il) EPPLER 360 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E360 rotorcraft airfoil Max thickness 12.2% at 36.9% chord Max camber 1.6% at 27.2% chord Max Cl/Cd 84 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m7-il) NACA M7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-7 airfoil Max thickness 6.2% at 40% chord Max camber 4.9% at 30% chord Max Cl/Cd 84 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh64-il) MH 64 8.59%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 64 for flying wings Max thickness 8.6% at 26.9% chord Max camber 1.4% at 41.8% chord Max Cl/Cd 84 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n63215b-il) NACA 63(2)-215 MOD B		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA-NASA/AMES/Hicks 63(2)-215 MOD B airfoil Max thickness 15% at 30% chord Max camber 1.5% at 10% chord Max Cl/Cd 83.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database