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.

(goe797-il) GOE 797 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 797 airfoil Max thickness 16% at 30% chord Max camber 4.9% at 40% chord Source UIUC Airfoil Coordinates Database
(mh93-il) MH 93 15.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 93 parafoil Max thickness 16% at 27.6% chord Max camber 1.4% at 15.2% chord Source UIUC Airfoil Coordinates Database
(mh94-il) MH 94 16.03%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 94 parafoil Max thickness 16% at 34.1% chord Max camber 1.3% at 74.1% chord Source UIUC Airfoil Coordinates Database
(r1082t-il) RONCZ 1082T VOYAGER TIP 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 1082T Voyager tip outer aft wing airfoil Max thickness 16% at 40% chord Max camber 3% at 40% chord Source UIUC Airfoil Coordinates Database
(s8036-il) S8036 (16%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8036 low Reynolds number airfoil Max thickness 16% at 36.8% chord Max camber 1.3% at 40.4% chord Source UIUC Airfoil Coordinates Database

(s8037-il) S8037 (16%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8037 low Reynolds number airfoil Max thickness 16% at 33.5% chord Max camber 1.9% at 40.4% chord Source UIUC Airfoil Coordinates Database
(s813-nr) NREL's S813 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S813 tip Max thickness 16% at 40.4% chord Max camber 2.3% at 54.4% chord Source NWTC National WInd Technology Center
(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 Source NWTC National WInd Technology Center
(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 Source NWTC National WInd Technology Center
(s822-nr) NREL's S822 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S822 tip 16.0% Dia=2 to 10 m Re=6.0E+5 Clmax(S)=1.00 Clmax(R)=0.98 Restrained max lift coef Max thickness 16% at 39.2% chord Max camber 1.8% at 59.5% chord Source NWTC National WInd Technology Center