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.

(rg15a213-il) RG 15A 2.5/13.0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 15A 2.5/13.0 airfoil Max thickness 13% at 30.2% chord Max camber 2.5% at 39.7% chord Source UIUC Airfoil Coordinates Database
(mb253515sm-il) MB253515 15.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Mike Bame MB253515 low Reynolds number airfoil Max thickness 15% at 35% chord Max camber 2.5% at 37.5% chord Source UIUC Airfoil Coordinates Database
(e205-il) E205 (10.48%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E205 low Reynolds number airfoil Max thickness 10.5% at 29.7% chord Max camber 2.5% at 38.7% chord Source UIUC Airfoil Coordinates Database
(nasasc2-0714-il) SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0714 airfoil (Ref. NASA TP-2890) Max thickness 13.9% at 37% chord Max camber 2.5% at 80% chord Source UIUC Airfoil Coordinates Database
(eh2510-il) EH 2.5/10		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.5/10 for tailless R/C aircraft Max thickness 10% at 30% chord Max camber 2.5% at 25% chord Source UIUC Airfoil Coordinates Database
(fx61140-il) FX 61-140 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-140 airfoil Max thickness 14% at 33.9% chord Max camber 2.5% at 30.9% chord Source UIUC Airfoil Coordinates Database
(dsma523b-il) DSMA-523B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	McDonnell/Douglas DSMA-523 transonic airfoil with blunt trailing edge Max thickness 11% at 36% chord Max camber 2.4% at 82% chord Source UIUC Airfoil Coordinates Database
(clarkys-il) CLARK YS AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YS airfoil Max thickness 11.7% at 30% chord Max camber 2.4% at 30% chord Source UIUC Airfoil Coordinates Database
(whitcomb-il) WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley Whitcomb integral supercritical airfoil Max thickness 11% at 35% chord Max camber 2.4% at 82.5% chord Source UIUC Airfoil Coordinates Database
(s808-nr) NREL's S808 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S808 root Max thickness 21% at 24.4% chord Max camber 2.4% at 72.9% chord Source NWTC National WInd Technology Center

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