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.

(mh92-il) MH 92 15.49%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 92 parafoil Max thickness 15.5% at 27.4% chord Max camber 1.4% at 15.1% chord Source UIUC Airfoil Coordinates Database
(ncambre-il) ONERA NACA CAMBRE AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale NACA-CAMBRE rotorcraft airfoil Max thickness 11.5% at 31.2% chord Max camber 1.4% at 15.9% chord Source UIUC Airfoil Coordinates Database
(mh91-il) MH 91 14.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 91 parafoil Max thickness 15% at 27.3% chord Max camber 1.4% at 18.7% chord Source UIUC Airfoil Coordinates Database
(ames01-il) NASA/AMES A-01 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Hicks A-01 transonic rotorcraft airfoil Max thickness 10.3% at 35% chord Max camber 1.4% at 15% chord Source UIUC Airfoil Coordinates Database
(sc20414-il) NASA SC(2)-0414 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0414 airfoil (NASA TP-2969) Max thickness 14% at 36% chord Max camber 1.5% at 83% chord Source UIUC Airfoil Coordinates Database
(s2062-il) S2062 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2062 low Reynolds number airfoil Max thickness 8% at 30.1% chord Max camber 1.5% at 49.6% chord Source UIUC Airfoil Coordinates Database
(goe599-il) GOE 599 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 599 airfoil Max thickness 10% at 29.6% chord Max camber 1.5% at 59.7% chord Source UIUC Airfoil Coordinates Database
(goe767-il) GOE 767 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 767 airfoil Max thickness 12% at 20% chord Max camber 1.5% at 20% chord Source UIUC Airfoil Coordinates Database
(eh1590-il) EH 1.5/9.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.5/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 1.5% at 25.9% chord Source UIUC Airfoil Coordinates Database
(goe766-il) GOE 766 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 766 airfoil Max thickness 12% at 25% chord Max camber 1.5% at 20% chord Source UIUC Airfoil Coordinates Database

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