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.

(mh115-il) MH 115 11.06%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 115 for a propeller for ultralight Max thickness 11.1% at 29.8% chord Max camber 5.5% at 46% chord Source UIUC Airfoil Coordinates Database
(goe323-il) GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 323 (Hansa-Brandenburg V.1) airfoil Max thickness 11.1% at 29.8% chord Max camber 5.2% at 29.8% chord Source UIUC Airfoil Coordinates Database
(mh70-il) MH 70 11.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 70 for fying wing (full size) Max thickness 11.1% at 29.4% chord Max camber 3% at 39.6% chord Source UIUC Airfoil Coordinates Database
(goe405-il) GOE 405 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 405 airfoil Max thickness 11.1% at 30% chord Max camber 6.5% at 40% chord Source UIUC Airfoil Coordinates Database
(e598-il) EPPLER 598 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E598 airfoil Max thickness 11.1% at 24.2% chord Max camber 4.5% at 34.4% chord Source UIUC Airfoil Coordinates Database
(c5d-il) LOCKHEED C-5A BL758.6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 60% chord Source UIUC Airfoil Coordinates Database
(goe363-il) GOE 363 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 363 airfoil Max thickness 11.1% at 19.8% chord Max camber 5.7% at 39.8% chord Source UIUC Airfoil Coordinates Database
(c5c-il) LOCKHEED C-5A BL576 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 65% chord Source UIUC Airfoil Coordinates Database
(npl9510-il) NPL 9510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9510 transonic airfoil Max thickness 11.1% at 32% chord Max camber 1.6% at 80% chord Source UIUC Airfoil Coordinates Database
(goe509-il) GOE 509 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 509 airfoil Max thickness 11.1% at 29.9% chord Max camber 5.2% at 39.9% chord Source UIUC Airfoil Coordinates Database

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