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.

(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 129.5 at Re# 1,000,000 Source NWTC National WInd Technology Center
(s1221-flap-il) S1221 w/ 4 deg flap		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1221 airfoil with 4 deg flap Max thickness 12.1% at 21.8% chord Max camber 5.3% at 52.9% chord Max Cl/Cd 129.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx63120-il) FX 63-120 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-120 airfoil Max thickness 12% at 30.8% chord Max camber 5.2% at 50% chord Max Cl/Cd 129.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(gs1-il) SIKORSKY GS-1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gluharoff/Sikorsky GS-1 airfoil Max thickness 13.9% at 30% chord Max camber 4.1% at 50% chord Max Cl/Cd 129.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(clarkv-il) CLARK V AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK V airfoil Max thickness 11.6% at 30% chord Max camber 3.4% at 50% chord Max Cl/Cd 129.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(e562-il) EPPLER 562 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E562 general aviation airfoil Max thickness 15% at 27.6% chord Max camber 4% at 50.8% chord Max Cl/Cd 129.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca4412-il) NACA 4412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4412 airfoil Max thickness 12% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 129.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx73cl3152-il) FX 73-CL3-152		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 73-CL3-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 8% at 43.5% chord Max Cl/Cd 129.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m24-il) NACA M24 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-24 airfoil Max thickness 12% at 30.1% chord Max camber 6.3% at 30.1% chord Max Cl/Cd 129.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s7055-il) S7055 (10.5%) Flat-Bottomed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S7055 low Reynolds number airfoil Max thickness 10.5% at 31.8% chord Max camber 3.3% at 38.6% chord Max Cl/Cd 129.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database