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.

(sc20403-il) NASA SC(2)-0403 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0403 airfoil (NASA TP-2969) Max thickness 3% at 36% chord Max camber 0.6% at 85% chord Max Cl/Cd 42.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(dh4009sm-il) dh4009sm		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dale House DH4009 (smoothed) used on the Storm R/C aerobatic aircraft Max thickness 8.9% at 41.6% chord Max camber 0.2% at 9.6% chord Max Cl/Cd 42.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe780-il) GOE 780 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 780 airfoil Max thickness 12% at 50% chord Max camber 1% at 40% chord Max Cl/Cd 42.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s1014-il) S1014		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1014 HPV airfoil Max thickness 16.5% at 42.2% chord Max camber 0% at 0% chord Max Cl/Cd 42 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s1016-il) S1016		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1016 HPV airfoil Max thickness 17.5% at 41.8% chord Max camber 0% at 0% chord Max Cl/Cd 41.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe388-il) GOE 388 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 388 airfoil Max thickness 10.2% at 29.9% chord Max camber 5.4% at 39.9% chord Max Cl/Cd 41.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sc20404-il) NASA SC(2)-0404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0404 airfoil (NASA TP-2969) Max thickness 4% at 37% chord Max camber 0.7% at 81% chord Max Cl/Cd 41.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(dga1182-il) D.G.A. 1182		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	D.G.A. 1182 airfoil Max thickness 7.6% at 30% chord Max camber 0.9% at 20% chord Max Cl/Cd 41.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(dbln526-il) SIKORSKY DBLN-526 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky DBLN-526 double ended rotorcraft airfoil Max thickness 26% at 50% chord Max camber 4% at 50% chord Max Cl/Cd 41.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca16006-il) NACA 16-006		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-006 airfoil Max thickness 6% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 41.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database