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.

(ah80136-il) AH 80-136		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 80-136 airfoil Max thickness 13.5% at 33.9% chord Max camber 3.4% at 33.9% chord Max Cl/Cd 105.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e205-il) E205 (10.48%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E205 low Reynolds number airfoil Max thickness 10.5% at 29.7% chord Max camber 2.5% at 38.7% chord Max Cl/Cd 105.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx66s196-il) FX 66-S-196 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-S-196 airfoil Max thickness 19.6% at 37.1% chord Max camber 3.8% at 43.5% chord Max Cl/Cd 105.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s820-nr) NREL's S820 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S820 tip 16.0% Dia=10 to 20 m Re=1.3E+6 Clmax(S)=1.10 Clmax(R)=1.06 Restrained max lift coef Max thickness 16% at 45.1% chord Max camber 2.1% at 59.7% chord Max Cl/Cd 105.3 at Re# 500,000 Source NWTC National WInd Technology Center
(goe497-il) GOE 497 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 497 airfoil Max thickness 12.7% at 30% chord Max camber 5.3% at 50% chord Max Cl/Cd 105.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe392-il) GOE 392 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 392 airfoil Max thickness 10.2% at 30% chord Max camber 4.8% at 40% chord Max Cl/Cd 105.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe417-il) GOE 417 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 417 airfoil Max thickness 6% at 20% chord Max camber 6.1% at 40% chord Max Cl/Cd 105.3 at Re# 500,000 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 105.3 at Re# 500,000 Source NWTC National WInd Technology Center
(goe360-il) GOE 360 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 360 airfoil Max thickness 9.7% at 29.9% chord Max camber 5.9% at 29.9% chord Max Cl/Cd 105.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe321-il) GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 321 (Hansa-Brandenburg III.1) airfoil Max thickness 11.2% at 29.9% chord Max camber 5.1% at 29.9% chord Max Cl/Cd 105.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database