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.

(r1080-il) RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1080 Voyager inner aft wing airfoil Max thickness 18% at 40% chord Max camber 3.3% at 40% chord Source UIUC Airfoil Coordinates Database
(r1082-il) RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1082 Voyager root outer aft wing airfoil Max thickness 18% at 40% chord Max camber 3.4% at 40% chord Source UIUC Airfoil Coordinates Database
(s807-nr) NREL's S807 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S807 root Max thickness 18% at 28.7% chord Max camber 1.9% at 78.3% chord Source NWTC National WInd Technology Center
(s810-nr) NREL's S810 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S810 tip Max thickness 18% at 44.2% chord Max camber 0.9% at 10.9% chord Source NWTC National WInd Technology Center
(s831-nr) NREL's S831 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S831 tip 18.0% Dia=40 to 50 m Re=3.5E+6 Clmax(S)=1.50 Clmax(R)=1.48 High max lift coef Max thickness 18% at 44.2% chord Max camber 5% at 53.1% chord Source NWTC National WInd Technology Center

(s833-nr) NREL's S833 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S833 primary 18.0% Dia=1 to 3 m Re=4.0E+5 Clmax(S)=1.10 Clmax(R)=1.13 High max lift coef Max thickness 18% at 36.3% chord Max camber 2.5% at 78.8% chord Source NWTC National WInd Technology Center
(sc20518-il) NASA SC(2)-0518 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0518 airfoil (NASA TP-2969) Max thickness 18% at 35% chord Max camber 1.9% at 82% chord Source UIUC Airfoil Coordinates Database
(usa34-il) USA 34 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-34 airfoil Max thickness 18% at 29.5% chord Max camber 7.7% at 39.5% chord Source UIUC Airfoil Coordinates Database
(e549-il) EPPLER 549 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E549 general aviation airfoil Max thickness 18.1% at 38.7% chord Max camber 2% at 34% chord Source UIUC Airfoil Coordinates Database
(e553-il) EPPLER 553 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E553 general aviation airfoil Max thickness 18.1% at 31.8% chord Max camber 2.9% at 56.6% chord Source UIUC Airfoil Coordinates Database