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.

(vr11x-il) BOEING-VERTOL VR-11X AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol/NASA/Dadone VR-11X transonic rotorcraft airfoil Max thickness 11% at 40% chord Max camber 2.4% at 25% 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
(ag26-il) AG26 Bubble Dancer DLG by Mark Drela		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG26 airfoil used on the Bubble Dancer R/C DLG Max thickness 6.8% at 23.3% chord Max camber 2.5% at 45.5% chord Source UIUC Airfoil Coordinates Database
(clarkyh-il) CLARK YH AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YH airfoil Max thickness 11.9% at 30% chord Max camber 2.5% at 30% chord Source UIUC Airfoil Coordinates Database
(davis-corrected-il) DAVIS BASIC B-24 WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Davis basic B-24 wing airfoil Max thickness 15.9% at 29.6% chord Max camber 2.5% at 29.6% chord Source UIUC Airfoil Coordinates Database
(doa5-il) DORNIER A-5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dornier A-5 airfoil (reconstruction) (DO 228 wing) Max thickness 16.2% at 40.1% chord Max camber 2.5% at 76% 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
(e207-il) E207 (12.04%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E207 low Reynolds number airfoil Max thickness 12% at 29.6% chord Max camber 2.5% at 38.6% chord Source UIUC Airfoil Coordinates Database
(e212-il) E212 (10.55%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E212 low Reynolds number airfoil Max thickness 10.6% at 27.5% chord Max camber 2.5% at 61.3% chord Source UIUC Airfoil Coordinates Database
(e231-il) E231		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E231 R/C sailplane airfoil Max thickness 12.3% at 39.4% chord Max camber 2.5% at 39.4% chord Source UIUC Airfoil Coordinates Database

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