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.

(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
(naca0008-il) NACA 0008		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% 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
(fx66h80-il) FX 66-H-80		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-H-80 airfoil Max thickness 8% at 27.9% chord Max camber 2.5% at 25% chord Source UIUC Airfoil Coordinates Database
(goe314-il) GOE 314 (HANSA-BRANDENBURG) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 314 (Hansa-Brandenburg) airfoil Max thickness 8% at 29.9% chord Max camber 4.7% at 29.9% chord Source UIUC Airfoil Coordinates Database
(hq258-il) HQ 2.5/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 2.5% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64208-il) NACA 64-208		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-208 airfoil Max thickness 8% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(rc08n1-il) NASA/LANGLEY RC-08(N)1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-08(N)1 rotorcraft airfoil Max thickness 8% at 37.5% chord Max camber 1.6% at 25% chord Source UIUC Airfoil Coordinates Database
(goe622-il) GOE 622 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 622 airfoil Max thickness 8% at 30% chord Max camber 2.4% at 40% chord Source UIUC Airfoil Coordinates Database
(rc08b3-il) NASA/LANGLEY RC-08(B)3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-08(B)3 rotorcraft airfoil Max thickness 8% at 37.8% chord Max camber 1.1% at 34.1% chord Source UIUC Airfoil Coordinates Database

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