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.

(nl722343-il) NLR-7223-43 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7223-43 transonic rotorcraft airfoil Max thickness 8.6% at 38% chord Max camber 1.3% at 74% chord Source UIUC Airfoil Coordinates Database
(rae69ck-il) RAE6-9CK AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE6-9CK transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Source UIUC Airfoil Coordinates Database
(tsagi8-il) TSAGI 8% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TSAGI 8% airfoil Max thickness 8% at 30% chord Max camber 1.3% at 30% chord Source UIUC Airfoil Coordinates Database
(giiii-il) GIII BL288 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 40% chord Max camber 1.3% at 25% chord Source UIUC Airfoil Coordinates Database
(pfcm-il) PROPFAN CRUISE MISSILE WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Propfan Cruise Missile wing airfoil Max thickness 8.2% at 40% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database
(giiih-il) GIII BL207 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 39.9% chord Max camber 1.3% at 29.9% chord Source UIUC Airfoil Coordinates Database
(p51htip-il) NACA 66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66 Max thickness 12% at 45% chord Max camber 1.3% at 47.5% chord Source UIUC Airfoil Coordinates Database
(giiig-il) GIII BL167 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 44.9% chord Max camber 1.3% at 29.9% chord Source UIUC Airfoil Coordinates Database
(p51hroot-il) NACA 66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66 Max thickness 15.5% at 45% chord Max camber 1.3% at 47.5% chord Source UIUC Airfoil Coordinates Database
(rae2822-il) RAE 2822 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 2822 transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Source UIUC Airfoil Coordinates Database

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