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.

(e330-il) EPPLER 330 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E330 flying wing airfoil Max thickness 11% at 29.2% chord Max camber 2.1% at 16.9% chord Max Cl/Cd 61.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca644421-il) NACA 64(4)-421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(4)-421 airfoil Max thickness 20.9% at 34.8% chord Max camber 2.2% at 50% chord Max Cl/Cd 61.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n2415-il) NACA 2415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2415 airfoil Max thickness 15% at 29.5% chord Max camber 2% at 39.6% chord Max Cl/Cd 61.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s6063-il) S6063 7.05%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S6063 low Reynolds number airfoil Max thickness 7% at 29.4% chord Max camber 1.3% at 43.8% chord Max Cl/Cd 61.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe599-il) GOE 599 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 599 airfoil Max thickness 10% at 29.6% chord Max camber 1.5% at 59.7% chord Max Cl/Cd 61.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(rc12b3-il) NASA/LANGLEY RC-12(B)3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-12(B)3 rotorcraft airfoil Max thickness 12% at 38% chord Max camber 2.2% at 34.3% chord Max Cl/Cd 61.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx77w153-il) WORTMANN FX 77-W-153 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-W-153 wind turbine airfoil Max thickness 15.2% at 27.9% chord Max camber 4.5% at 27.9% chord Max Cl/Cd 61.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh150-il) MH 150 23.89%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 150 for marine ruddershaft for torque reduction (schottel units) Max thickness 23.9% at 27.2% chord Max camber 4.5% at 53.8% chord Max Cl/Cd 61.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca634421-il) NACA 63(4)-421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(4)-421 airfoil Max thickness 21% at 34.8% chord Max camber 2.2% at 50% chord Max Cl/Cd 61.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe738-il) GOE 738 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 738 airfoil Max thickness 15.4% at 30% chord Max camber 2.1% at 30% chord Max Cl/Cd 61.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database