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.

(goe493-il) GOE 493 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 493 airfoil Max thickness 14.9% at 29.3% chord Max camber 3.4% at 49.3% chord Source UIUC Airfoil Coordinates Database
(goe559-il) GOE 559 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 559 airfoil Max thickness 11.2% at 30% chord Max camber 3.4% at 30% chord Source UIUC Airfoil Coordinates Database
(goe585-il) GOE 585 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 585 airfoil Max thickness 8.2% at 20% chord Max camber 3.4% at 40% chord Source UIUC Airfoil Coordinates Database
(goe670-il) GOE 670 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 670 airfoil Max thickness 9% at 30% chord Max camber 3.4% at 40% chord Source UIUC Airfoil Coordinates Database
(marske5-il) MARSKE MONARCH AIRFOIL (NACA 43012A)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Monarch airfoil (NACA 43012A) Max thickness 12.2% at 20% chord Max camber 3.4% at 15% chord Source UIUC Airfoil Coordinates Database
(mh122-il) MH 122 9.32%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 122 for tip section of a propeller Max thickness 9.3% at 37.6% chord Max camber 3.4% at 64.3% chord Source UIUC Airfoil Coordinates Database
(r1082-il) RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1082 Voyager root outer aft wing airfoil Max thickness 18% at 40% chord Max camber 3.4% at 40% chord Source UIUC Airfoil Coordinates Database
(s4083-il) S4083 (8%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4083 low Reynolds number airfoil Max thickness 8% at 22.5% chord Max camber 3.4% at 35.5% chord Source UIUC Airfoil Coordinates Database
(sd7032-il) SD7032-099-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7032 low Reynolds number airfoil Max thickness 10% at 26.6% chord Max camber 3.4% at 45.1% chord Source UIUC Airfoil Coordinates Database
(ua79sff-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 sailplane airfoil FLAP Max thickness 8.7% at 73.1% chord Max camber 3.4% at 78.1% chord Source UIUC Airfoil Coordinates Database

Page 90 of 164     80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 97 98 99     Next

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