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.

(s8064-il) S8064		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for Q-500 (Q500) pylon racing (12.33%). Used on the Great Planes Viper 500 ARF. Max thickness 12.3% at 37.8% chord Max camber 1.1% at 56.2% chord Source UIUC Airfoil Coordinates Database
(naca63206-il) NACA 63-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-206 airfoil Max thickness 6% at 35% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca65209-il) NACA 65-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(n63215-il) NACA 63-215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca65206-il) NACA 65-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(n63212-il) NACA 63-212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(1)-212 airfoil Max thickness 12% at 34.9% chord Max camber 1.1% at 55% chord Source UIUC Airfoil Coordinates Database
(n63210-il) NACA 63-210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-210 airfoil Max thickness 10% at 35% chord Max camber 1.1% at 60% chord Source UIUC Airfoil Coordinates Database
(ag47ct02r-il) AG47ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG47ct -02f airfoil Max thickness 5% at 22.5% chord Max camber 1.2% at 33.4% 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
(e182-il) E182 (8.47%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E182 low Reynolds number airfoil Max thickness 8.5% at 32.4% chord Max camber 1.2% at 37.5% chord Source UIUC Airfoil Coordinates Database

Page 27 of 164     17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36     Next

Please see the source web site or designer for any license conditions.