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.

(goe518-il) GOE 518 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 518 airfoil Max thickness 18% at 29.8% chord Max camber 7.3% at 29.8% chord Max Cl/Cd 79.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20710-il) NASA SC(2)-0710 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0710 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 2.1% at 81% chord Max Cl/Cd 79.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n64212ma-il) NACA 64(1)-212 MOD A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA-NASA/AMES/Hicks 63(1)-212 MOD A airfoil Max thickness 12% at 41.2% chord Max camber 2.5% at 21.5% chord Max Cl/Cd 79.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca652215-il) NACA 65(2)-215		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(2)-215 airfoil Max thickness 15% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 79 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rae2822-il) RAE 2822 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 2822 transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Max Cl/Cd 79 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(rae69ck-il) RAE6-9CK AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE6-9CK transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Max Cl/Cd 79 at Re# 1,000,000 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 Max Cl/Cd 79 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx76120-il) WORTMANN FX 76-120		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-120 symmetrical airfoil Max thickness 12.1% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 78.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca1410-il) NACA 1410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1410 airfoil Max thickness 10% at 29.9% chord Max camber 1% at 50% chord Max Cl/Cd 78.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(joukowsk0021-jf) Joukovsky f=0% t=21%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	Joukowski 21% symmetrical airfoil Max thickness 21% at 26.6% chord Max camber 0% at 0% chord Max Cl/Cd 78.9 at Re# 1,000,000 Source Javafoil generated