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.

(m7-il) NACA M7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-7 airfoil Max thickness 6.2% at 40% chord Max camber 4.9% at 30% chord Max Cl/Cd 68.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s6061-il) S6061 9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S6061 low Reynolds number airfoil Max thickness 9% at 34% chord Max camber 1.5% at 43.6% chord Max Cl/Cd 68.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e638-il) EPPLER 638 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E638 airfoil Max thickness 12.4% at 28.5% chord Max camber 4.4% at 24.5% chord Max Cl/Cd 68.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(raf6-il) RAF 6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-6 airfoil Max thickness 10% at 30% chord Max camber 4.6% at 30% chord Max Cl/Cd 68.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe421-il) GOE 421 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 421 airfoil Max thickness 19% at 29.3% chord Max camber 8.1% at 49.3% chord Max Cl/Cd 68.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe398-il) GOE 398 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 398 airfoil Max thickness 13.9% at 30% chord Max camber 4.9% at 40% chord Max Cl/Cd 68.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e1200-il) EPPLER 1200 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1200 general aviation airfoil Max thickness 16.9% at 36.1% chord Max camber 3.5% at 50.2% chord Max Cl/Cd 68.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n6h10-il) NACA 6-H-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6-H-10 rotorcraft airfoil Max thickness 10% at 40% chord Max camber 4.6% at 40% chord Max Cl/Cd 68.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx60160-il) FX 60-160 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-160 airfoil Max thickness 15.6% at 40% chord Max camber 3.1% at 60% chord Max Cl/Cd 68.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sg6040-il) SG6040		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6040 wind turbine airfoil Max thickness 16% at 35.3% chord Max camber 2.3% at 60.5% chord Max Cl/Cd 68.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database