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.

(m17-il) NACA M17 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-17 airfoil Max thickness 8.1% at 40% chord Max camber 4.1% at 30% chord Source UIUC Airfoil Coordinates Database
(m14-il) NACA M14 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-14 airfoil Max thickness 8.1% at 30% chord Max camber 3.9% at 30% chord Source UIUC Airfoil Coordinates Database
(2032c-il) 20-32C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dillner 20-32-C low Reynolds number airfoil Max thickness 8% at 20% chord Max camber 6.9% at 40% chord Source UIUC Airfoil Coordinates Database
(fx77080-il) WORTMANN FX 77-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-080 symmetrical airfoil Max thickness 8% at 27.9% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s2062-il) S2062 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2062 low Reynolds number airfoil Max thickness 8% at 30.1% chord Max camber 1.5% at 49.6% chord Source UIUC Airfoil Coordinates Database
(hq308-il) HQ 3.0/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 3% at 50% chord Source UIUC Airfoil Coordinates Database
(s8025-il) S8025 (8%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8025 low Reynolds number airfoil Max thickness 8% at 22.9% chord Max camber 0.4% at 18.8% chord Source UIUC Airfoil Coordinates Database
(s2060-il) S2060 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2060 low Reynolds number airfoil Max thickness 8% at 30.2% chord Max camber 1.6% at 49.7% chord Source UIUC Airfoil Coordinates Database
(s2055-il) S2055		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2055 low Reynolds number airfoil Max thickness 8% at 34.8% chord Max camber 1.4% at 44.6% chord Source UIUC Airfoil Coordinates Database
(naca000834-il) NACA 0008-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database

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