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.

(sc20518-il) NASA SC(2)-0518 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0518 airfoil (NASA TP-2969) Max thickness 18% at 35% chord Max camber 1.9% at 82% chord Max Cl/Cd 77.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(dsma523b-il) DSMA-523B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	McDonnell/Douglas DSMA-523 transonic airfoil with blunt trailing edge Max thickness 11% at 36% chord Max camber 2.4% at 82% chord Max Cl/Cd 77.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca1408-il) NACA 1408		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1408 airfoil Max thickness 8% at 30% chord Max camber 1% at 40% chord Max Cl/Cd 77.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(c5e-il) LOCKHEED C-5A BL1256 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 10.8% at 40% chord Max camber 1.4% at 30% chord Max Cl/Cd 77.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(giiia-il) GIII BL0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 11% at 39.7% chord Max camber 0.7% at 14.7% chord Max Cl/Cd 77.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(c5b-il) LOCKHEED C-5A BL488.2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.5% at 40% chord Max camber 1.2% at 70% chord Max Cl/Cd 77.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe587-il) GOE 587 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 587 airfoil Max thickness 5.8% at 40% chord Max camber 3% at 30% chord Max Cl/Cd 77.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(dga1138-il) D.G.A. 1138		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	D.G.A. 1138 airfoil Max thickness 6.9% at 30% chord Max camber 2.6% at 40% chord Max Cl/Cd 77 at Re# 1,000,000 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 77 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(eh1070-il) Eh 1.0/7.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.0/7.0 for tailless R/C aircraft Max thickness 7% at 28.7% chord Max camber 1% at 25.9% chord Max Cl/Cd 77 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database