Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

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.

(naca24112-jf) NACA 24112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 24112 5 digit reflex airfoil Max thickness 12% at 29.4% chord Max camber 1.7% at 20.6% chord Max Cl/Cd 84.9 at Re# 500,000 Source Javafoil generated
(sd7080-il) SD7080 (9.2%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7080 low Reynolds number airfoil Max thickness 9.2% at 30% chord Max camber 2.1% at 44.4% chord Max Cl/Cd 84.9 at Re# 500,000 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 Max Cl/Cd 84.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s2046-il) S2046		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2046 low Reynolds number airfoil Max thickness 9% at 26.2% chord Max camber 2.6% at 55.1% chord Max Cl/Cd 84.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(m685-il) M6 (85%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M6 (85%) Max thickness 10.2% at 30% chord Max camber 1.9% at 30% chord Max Cl/Cd 84.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe614-il) GOE 614 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 614 airfoil Max thickness 18.8% at 29.2% chord Max camber 6.2% at 39.2% chord Max Cl/Cd 84.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe222-il) GOE 222 (MVA H.33) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 222 (MVA H.33) airfoil Max thickness 18.5% at 29.2% chord Max camber 7.2% at 49.2% chord Max Cl/Cd 84.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe510-il) GOE 510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 510 airfoil Max thickness 13.7% at 19.7% chord Max camber 5.8% at 39.7% chord Max Cl/Cd 84.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(eiffel430-il) Eiffel 430 (Lachassgne)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 430 (Lachassgne) airfoil Max thickness 9.7% at 15% chord Max camber 4.5% at 40% chord Max Cl/Cd 84.8 at Re# 500,000 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 Max Cl/Cd 84.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database