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.

(psu94097-il) PSU 94-097 (AIAA 2001-2478)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Maughmer PSU 94-097 winglet airfoil Max thickness 9.7% at 32.3% chord Max camber 4% at 46.3% chord Source UIUC Airfoil Coordinates Database
(rae5214-il) RAE 5214 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 5214 transonic airfoil Max thickness 9.7% at 35.5% chord Max camber 1.4% at 69.1% chord Source UIUC Airfoil Coordinates Database
(rae5215-il) RAE 5215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 5215 transonic airfoil Max thickness 9.7% at 35.5% chord Max camber 1.5% at 69.1% chord Source UIUC Airfoil Coordinates Database
(rhodesg30-il) Rhode St. Genese 30		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rhode St. Genese 30 airfoil Max thickness 9.7% at 30% chord Max camber 3.2% at 40% chord Source UIUC Airfoil Coordinates Database
(s4095-il) S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for micro RC soaring. Used on the E-flite UMX ASK-21 scale RC sailplane. Max thickness 9.7% at 29.1% chord Max camber 1.7% at 33.7% chord Source UIUC Airfoil Coordinates Database
(goe238-il) GOE 238 (HANSA-BRANDENBURG) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 238 (HANSA-BRANDENBURG) airfoil Max thickness 9.8% at 29.8% chord Max camber 5.5% at 29.8% chord Source UIUC Airfoil Coordinates Database
(goe303-il) GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 303 (Friedrichshafen G03) airfoil Max thickness 9.8% at 29.9% chord Max camber 5.9% at 39.9% chord Source UIUC Airfoil Coordinates Database
(goe596-il) GOE 596 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 596 airfoil Max thickness 9.8% at 30% chord Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database
(goe746-il) GOE 746 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 746 airfoil Max thickness 9.8% at 30% chord Max camber 5% at 30% chord Source UIUC Airfoil Coordinates Database
(goe801-il) GOE 801 (MVA 301) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 801 (MVA 301) airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Source UIUC Airfoil Coordinates Database

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