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.

(mh22-il) MH 22 7.2%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 22 for F3D Pylon Racing Max thickness 7.2% at 27% chord Max camber 1.8% at 37% chord Source UIUC Airfoil Coordinates Database
(naca23018-il) NACA 23018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23018 airfoil Max thickness 18% at 30% chord Max camber 1.8% at 15% chord Source UIUC Airfoil Coordinates Database
(naca23015-il) NACA 23015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23015 airfoil Max thickness 15% at 30% chord Max camber 1.8% at 15% chord Source UIUC Airfoil Coordinates Database
(ah21-9-il) AH21 9% version (Andrew Hollom)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Andrew Hollom AH 21 airfoil (original 9% version) Max thickness 7% at 34.9% chord Max camber 1.8% at 54.8% chord Source UIUC Airfoil Coordinates Database
(c141e-il) LOCKHEED C-141 BL761.11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10.5% at 40.2% chord Max camber 1.8% at 50% chord Source UIUC Airfoil Coordinates Database
(naca001264a08cli02-il) NACA 0012-64 a=0.8 c(li)=0.2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-64 a=0.8 c(li)=0.2 airfoil Max thickness 11% at 39.9% chord Max camber 1.8% at 29.9% chord Source UIUC Airfoil Coordinates Database
(naca23012-il) NACA 23012 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23012 airfoil Max thickness 12% at 29.8% chord Max camber 1.8% at 12.7% chord Source UIUC Airfoil Coordinates Database
(ag45ct02r-il) AG45ct -02f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG45ct -02f airfoil Max thickness 6.9% at 23.3% chord Max camber 1.8% at 33.1% chord Source UIUC Airfoil Coordinates Database
(pw98mod-pw) PW98-mod		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Modified PW51 with higher camber and therefore a higher clmax Max thickness 8.4% at 27.5% chord Max camber 1.8% at 27.5% chord Source RC Groups
(s3016-il) S3016-095-87		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3016 low Reynolds number airfoil Max thickness 9.5% at 28.9% chord Max camber 1.8% at 43.1% chord Source UIUC Airfoil Coordinates Database

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