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.

(goe676-il) GOE 676 (= M 12) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 676 (= M 12) airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Source UIUC Airfoil Coordinates Database
(hh02-il) HUGHES HELICOPTERS HH-02 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hughes helicopters HH-02 rotorcraft airfoil Max thickness 9.6% at 30% chord Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database
(hq2010-il) HQ 2.0/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 2% at 45% chord Source UIUC Airfoil Coordinates Database
(hq2012-il) HQ 2.0/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2% at 50% chord Source UIUC Airfoil Coordinates Database
(hq208-il) HQ 2.0/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 2% at 50% chord Source UIUC Airfoil Coordinates Database
(hq209-il) HQ 2.0/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 2% at 50% chord Source UIUC Airfoil Coordinates Database
(hq2090sm-il) HQ-2.0/9 9.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/9 R/C sailplane airfoil (smoothed) Max thickness 9% at 35% chord Max camber 2% at 50% chord Source UIUC Airfoil Coordinates Database
(l188root-il) LOCKHEED L-188 ROOT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed L-188/P-3 root airfoil NACA 0014 -1.10 40/1.051 Cli=.3 a=.8 Max thickness 14% at 41.3% chord Max camber 2% at 51.7% chord Source UIUC Airfoil Coordinates Database
(m12-il) NACA M12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-12 airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% 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

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