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.

(oaf117-il) OAF117 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF117 Fenestron airfoil Max thickness 11.5% at 23.2% chord Max camber 2% at 46.9% chord Source UIUC Airfoil Coordinates Database
(naca2412-il) NACA 2412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2412 airfoil Max thickness 12% at 30% chord Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database
(e549-il) EPPLER 549 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E549 general aviation airfoil Max thickness 18.1% at 38.7% chord Max camber 2% at 34% chord Source UIUC Airfoil Coordinates Database
(ag45c03-il) AG45c -03f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG45c -03f airfoil Max thickness 6.9% at 23.5% chord Max camber 2% at 31.7% chord Source UIUC Airfoil Coordinates Database
(tsagi12-il) TSAGI 12% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TSAGI 12% airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Source UIUC Airfoil Coordinates Database
(n2415-il) NACA 2415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2415 airfoil Max thickness 15% at 29.5% chord Max camber 2% at 39.6% chord Source UIUC Airfoil Coordinates Database
(n2414-il) NACA 2414		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2414 airfoil Max thickness 14% at 29.5% chord Max camber 2% at 39.6% chord Source UIUC Airfoil Coordinates Database
(naca2410-il) NACA 2410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2410 airfoil Max thickness 10% at 29.9% chord Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database
(e547-il) EPPLER 547 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E547 general aviation airfoil Max thickness 17.4% at 40.3% chord Max camber 2% at 30.7% chord Source UIUC Airfoil Coordinates Database
(naca2408-il) NACA 2408		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2408 airfoil Max thickness 8% at 29.9% chord Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database

Page 51 of 164     41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60     Next

Please see the source web site or designer for any license conditions.