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.

(mh94-il) MH 94 16.03%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 94 parafoil Max thickness 16% at 34.1% chord Max camber 1.3% at 74.1% chord Source UIUC Airfoil Coordinates Database
(nl722362-il) NLR-7223-62 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7223-62 transonic rotorcraft airfoil Max thickness 8.6% at 38% chord Max camber 1.3% at 21.6% chord Source UIUC Airfoil Coordinates Database
(nl722343-il) NLR-7223-43 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7223-43 transonic rotorcraft airfoil Max thickness 8.6% at 38% chord Max camber 1.3% at 74% chord Source UIUC Airfoil Coordinates Database
(goe416a-il) GOE 416A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 416A airfoil Max thickness 11.7% at 29.5% chord Max camber 1.3% at 59.6% chord Source UIUC Airfoil Coordinates Database
(sc20606-il) NASA SC(2)-0606 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0606 airfoil (NASA TP-2969) Max thickness 6% at 34% chord Max camber 1.3% at 81% chord Source UIUC Airfoil Coordinates Database
(pfcm-il) PROPFAN CRUISE MISSILE WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Propfan Cruise Missile wing airfoil Max thickness 8.2% at 40% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database
(p51htip-il) NACA 66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66 Max thickness 12% at 45% chord Max camber 1.3% at 47.5% chord Source UIUC Airfoil Coordinates Database
(v13009-il) BOEING VERTOL V(1.95)3009-1.25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V(1.9)3006-1.25 rotorcraft airfoil Max thickness 9% at 30.1% chord Max camber 1.3% at 20.1% chord Source UIUC Airfoil Coordinates Database
(ag47ct02r-il) AG47ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG47ct -02f airfoil Max thickness 5% at 22.5% chord Max camber 1.2% at 33.4% chord Source UIUC Airfoil Coordinates Database
(vr8b-il) BOEING-VERTOL VR-8 AIRFOIL WITH TAB		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-8 rotorcraft airfoil with tab Max thickness 8.2% at 35% chord Max camber 1.2% at 35% chord Source UIUC Airfoil Coordinates Database

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