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.

(e472-il) EPPLER 472 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E472 aerobatic aircraft airfoil Max thickness 12.1% at 17.5% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca16006-il) NACA 16-006		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-006 airfoil Max thickness 6% at 50% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n0011sc-il) NACA/LANGLEY SYMMETRICAL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 11% symmetrical supercritical airfoil Max thickness 11% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(rae101-il) RAE 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 101 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(rae102-il) RAE 102 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 102 airfoil Max thickness 10% at 36% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n0009sm-il) NACA-0009 9.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0009 airfoil (smoothed) Max thickness 9% at 30.9% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(rae100-il) RAE 100 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 100 airfoil Max thickness 10% at 26% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s1048-il) S1048 14% (Danny Howell)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1048 airfoil Max thickness 14% at 27% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64015a-il) NACA 642-015A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-015A airfoil Max thickness 15% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(fx71l150-il) FX 71-L-150/30 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-L-150/30 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database

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