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.

(goe310-il) GOE 310 (MVA H.42) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 310 (MVA H.42) airfoil Max thickness 8.1% at 29.9% chord Max camber 4.8% at 39.9% chord Source UIUC Airfoil Coordinates Database
(fx80080-il) WORTMANN FX 80-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 80-080 airfoil Max thickness 8.1% at 40.2% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(goe308-il) GOE 308 (MVA H.40) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 308 (MVA H.40) airfoil Max thickness 8.1% at 29.9% chord Max camber 5% at 29.9% chord Source UIUC Airfoil Coordinates Database
(m23-il) NACA M23 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-23 airfoil Max thickness 8.1% at 30.1% chord Max camber 6.4% at 30.1% chord Source UIUC Airfoil Coordinates Database
(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
(goe326-il) GOE 326 (PFALZ 55) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 326 (Pfalz 55) airfoil Max thickness 8.2% at 29.9% chord Max camber 4.7% at 39.9% chord Source UIUC Airfoil Coordinates Database
(m11-il) NACA M11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-11 airfoil Max thickness 8.2% at 30% chord Max camber 1.9% at 30% chord Source UIUC Airfoil Coordinates Database
(goe325-il) GOE 325 (PFALZ 54) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 325 (Pfalz 54) airfoil Max thickness 8.2% at 20% chord Max camber 4.6% at 30% chord Source UIUC Airfoil Coordinates Database
(vr8b-il) BOEING-VERTOL VR-8 AIRFOIL WITH TAB		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-8 rotorcraft airfoil with tab Max thickness 8.2% at 35% chord Max camber 1.2% at 35% chord Source UIUC Airfoil Coordinates Database

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