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.

(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 Max Cl/Cd 91.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca654221-il) NACA 65(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-221 airfoil Max thickness 21% at 39.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 91.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe116-il) GOE 116 (MVA MK.3) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 116 (MVA MK.3) airfoil Max thickness 9.3% at 39.8% chord Max camber 4.1% at 39.8% chord Max Cl/Cd 91.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(rc410-il) NASA RC(4)-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC(4)-10 rotorcraft airfoil Max thickness 10% at 37.8% chord Max camber 2.1% at 30.3% chord Max Cl/Cd 91.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ag11-il) AG11		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG11 airfoil Max thickness 5.8% at 26% chord Max camber 2.2% at 29.7% chord Max Cl/Cd 91.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(naca664221-il) NACA 66(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(4)-221 airfoil Max thickness 21% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 91.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc1095r8-il) SIKORSKY SC1094R8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Velkoff SC1095 R8 rotorcraft airfoil Max thickness 9.3% at 26.5% chord Max camber 2.1% at 20.5% chord Max Cl/Cd 91.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e180-il) E180 (8.59%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E180 low Reynolds number airfoil Max thickness 8.6% at 33.5% chord Max camber 2% at 38.1% chord Max Cl/Cd 91.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc2110-il) SIKORSKY SC2110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Lednicer & Owen SC2110 rotorcraft airfoil (SC5410) Max thickness 9.9% at 37.7% chord Max camber 1.9% at 15.7% chord Max Cl/Cd 91.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e472-il) EPPLER 472 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E472 aerobatic aircraft airfoil Max thickness 12.1% at 17.5% chord Max camber 0% at 0% chord Max Cl/Cd 91.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database