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.

(giiin-il) GIII BL450 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.4% at 30.2% chord Max camber 2.1% at 20.2% chord Source UIUC Airfoil Coordinates Database
(s102s-il) SOMERS S102 AIRFOIL (SHARP)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord Max camber 2.1% at 68.7% chord Source UIUC Airfoil Coordinates Database
(hq2195-il) HQ 2.1/9.5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.1/9.5 R/C sailplane airfoil Max thickness 9.5% at 35% chord Max camber 2.1% at 55% chord Source UIUC Airfoil Coordinates Database
(e222-il) E222 (10.17%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E222 low Reynolds number airfoil Max thickness 10.2% at 31.1% chord Max camber 2.1% at 55.3% chord Source UIUC Airfoil Coordinates Database
(e1214-il) EPPLER 1214 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1214 general aviation airfoil Max thickness 19.8% at 26.2% chord Max camber 2.1% at 30.4% chord Source UIUC Airfoil Coordinates Database

(e1213-il) EPPLER 1213 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1213 general aviation airfoil Max thickness 17.4% at 22.1% chord Max camber 2.1% at 35.1% chord 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 Source NWTC National WInd Technology Center
(sc20710-il) NASA SC(2)-0710 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0710 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 2.1% at 81% chord Source UIUC Airfoil Coordinates Database
(s9000-il) S9000 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9000 (9%) low Reynolds number airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 28.2% chord Max camber 2.1% at 44.8% chord Source UIUC Airfoil Coordinates Database
(sc20614-il) NASA SC(2)-0614 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0614 airfoil (NASA TP-2969) Max thickness 14% at 36% chord Max camber 2.1% at 81% chord Source UIUC Airfoil Coordinates Database