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.

(fx74cl5140-il) FX74_CL5_140		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 74-CL5-140 high lift airfoil Max thickness 14% at 30.9% chord Max camber 9.9% at 37.1% chord Max Cl/Cd 118.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe123-il) GOE 123 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 123 airfoil Max thickness 5.4% at 25% chord Max camber 5.7% at 40% chord Max Cl/Cd 118.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s801-nr) NREL's S801 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S801 primary 13.5% Not recommended Max thickness 13.5% at 37.8% chord Max camber 3.7% at 47.1% chord Max Cl/Cd 118.8 at Re# 500,000 Source NWTC National WInd Technology Center
(fx74modsm-il) FX 74-Cl5-140 MOD (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Modified Wortmann FX 74-CL5-140 high lift airfoil Max thickness 13.1% at 27.1% chord Max camber 9.7% at 41.6% chord Max Cl/Cd 118.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n6409-il) NACA6409 9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6409 Max thickness 9% at 29.3% chord Max camber 6% at 39.6% chord Max Cl/Cd 118.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(e379-il) EPPLER 379 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E379 ultralight airfoil Max thickness 2.2% at 5.8% chord Max camber 8% at 31.8% chord Max Cl/Cd 118.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s803-nr) NREL's S803 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S803 tip Not recommended Max thickness 11.5% at 37.5% chord Max camber 3.7% at 46.9% chord Max Cl/Cd 118.4 at Re# 500,000 Source NWTC National WInd Technology Center
(fx63110-il) FX 63-110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-110 airfoil Max thickness 11% at 30.8% chord Max camber 4.3% at 50% chord Max Cl/Cd 118.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe227-il) GOE 227 (MVA H.37) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 227 (MVA H.37) airfoil Max thickness 14.6% at 25% chord Max camber 7.8% at 50% chord Max Cl/Cd 118.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe499-il) GOE 499 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 499 airfoil Max thickness 6.8% at 30% chord Max camber 5.9% at 50% chord Max Cl/Cd 118.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database