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.

(ls421mod-il) NASA/LANGLEY LS(1)-0421MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0421MOD general aviation airfoil Max thickness 21% at 32.5% chord Max camber 2.3% at 30% chord Max Cl/Cd 80.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe625-il) GOE 625 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 625 airfoil Max thickness 20% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 80.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s5010-il) S5010		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S5010 low Reynolds number airfoil Max thickness 9.8% at 27.6% chord Max camber 1.8% at 32% chord Max Cl/Cd 80.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(usa51-il) USA 51 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-51 airfoil Max thickness 9.3% at 30% chord Max camber 2.6% at 30% chord Max Cl/Cd 80.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(usa29-il) USA 29 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-29 airfoil Max thickness 13.2% at 29.7% chord Max camber 5.5% at 39.7% chord Max Cl/Cd 80.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(naca001264a08cli02-il) NACA 0012-64 a=0.8 c(li)=0.2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-64 a=0.8 c(li)=0.2 airfoil Max thickness 11% at 39.9% chord Max camber 1.8% at 29.9% chord Max Cl/Cd 80.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe648-il) GOE 648 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 648 airfoil Max thickness 15.2% at 29.4% chord Max camber 3.9% at 39.4% chord Max Cl/Cd 80.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e341-il) EPPLER 341 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E341 flying wing airfoil Max thickness 13.9% at 32.8% chord Max camber 3% at 23.2% chord Max Cl/Cd 80.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe565-il) GOE 565 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 565 airfoil Max thickness 8.4% at 30% chord Max camber 2.8% at 50% chord Max Cl/Cd 80.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sd6060-il) SD6060-104-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD6060 low Reynolds number airfoil Max thickness 10.4% at 33.9% chord Max camber 1.6% at 38.6% chord Max Cl/Cd 80.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database