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.

(e582-il) EPPLER 582 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E582 sailplane airfoil Max thickness 14.7% at 37.8% chord Max camber 4.2% at 43.1% chord Max Cl/Cd 45.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca633418-il) NACA 63		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63 Max thickness 18% at 33.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 45.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rc1064c-il) NASA/LANGLEY RC10-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 10-64C rotorcraft airfoil Max thickness 10% at 40% chord Max camber 1% at 35% chord Max Cl/Cd 45.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe344-il) GOE 344 (PFALZ 71) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 344 (Pfalz 71) airfoil Max thickness 7.2% at 19.9% chord Max camber 2.7% at 39.9% chord Max Cl/Cd 45.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e553-il) EPPLER 553 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E553 general aviation airfoil Max thickness 18.1% at 31.8% chord Max camber 2.9% at 56.6% chord Max Cl/Cd 45.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(fx69h098-il) BELL/WORTMANN FX 69-H-098 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell/Wortmann FX 69-H-098 rotorcraft airfoil Max thickness 9.9% at 28.2% chord Max camber 1.7% at 22.5% chord Max Cl/Cd 45.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(giiid-il) GIII BL86 AIRFOIL (modified line 31)		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 9.7% at 39.8% chord Max camber 1% at 29.8% chord Max Cl/Cd 45.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(usa40b-il) USA 40 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-40B airfoil Max thickness 13.6% at 20% chord Max camber 4% at 40% chord Max Cl/Cd 45.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag04-il) AG04		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG04 airfoil Max thickness 6.4% at 22.5% chord Max camber 1.7% at 41.5% chord Max Cl/Cd 45.3 at Re# 100,000 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 45.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database