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.

(s816-nr) NREL's S816 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S816 primary 21.0% Dia=30 to 50 m Re=4.0E+6 Clmax(S)=1.20 Clmax(R)=1.17 Restrained max lift coef Max thickness 21% at 39% chord Max camber 1.8% at 67.6% chord Max Cl/Cd 96.9 at Re# 500,000 Source NWTC National WInd Technology Center
(goe328-il) GOE 328 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 328 airfoil Max thickness 8.2% at 30% chord Max camber 4.3% at 30% chord Max Cl/Cd 96.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx60160-il) FX 60-160 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-160 airfoil Max thickness 15.6% at 40% chord Max camber 3.1% at 60% chord Max Cl/Cd 96.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe207-il) GOE 207 (AVIATIK V8) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 207 (AVIATIK V8) airfoil Max thickness 8.8% at 19.9% chord Max camber 6.6% at 29.9% chord Max Cl/Cd 96.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s805a-nr) NREL's S805A Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S805A primary Max thickness 13.5% at 40% chord Max camber 2.1% at 35% chord Max Cl/Cd 96.9 at Re# 500,000 Source NWTC National WInd Technology Center

(goe279-il) GOE 279 (DAIMLER X) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 279 (DAIMLER X) airfoil Max thickness 7.4% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 96.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fxs21158-il) FX S 02/1-158 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX S 02/1-158 airfoil Max thickness 15.8% at 30.9% chord Max camber 3.5% at 37.1% chord Max Cl/Cd 96.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fxs03182-il) FX S 03-182 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX S 03-182 airfoil Max thickness 18.2% at 40.2% chord Max camber 2.9% at 56.5% chord Max Cl/Cd 96.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s3024-il) AIRFOIL 3024 9.84%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3024 low Reynolds number airfoil Max thickness 9.8% at 30.7% chord Max camber 3% at 44.7% chord Max Cl/Cd 96.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe436-il) GOE 436 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 436 airfoil Max thickness 11% at 30% chord Max camber 3.8% at 30% chord Max Cl/Cd 96.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database