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.

(usa35a-il) USA 35 A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-35A airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord Max Cl/Cd 122.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m17-il) NACA M17 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-17 airfoil Max thickness 8.1% at 40% chord Max camber 4.1% at 30% chord Max Cl/Cd 122.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e214-il) E214 (11.1%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E214 low Reynolds number airfoil Max thickness 11.1% at 33.1% chord Max camber 3.7% at 56.9% chord Max Cl/Cd 122.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe803h-il) GOE 803 (HACKLINGER) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 803 (Hacklinger) airfoil Max thickness 6.3% at 15% chord Max camber 6.6% at 40% chord Max Cl/Cd 122.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s4320-il) S4320		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4320 low Reynolds number airfoil Max thickness 9.4% at 26.8% chord Max camber 4.5% at 40.2% chord Max Cl/Cd 122.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe303-il) GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 303 (Friedrichshafen G03) airfoil Max thickness 9.8% at 29.9% chord Max camber 5.9% at 39.9% chord Max Cl/Cd 122.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e557-il) EPPLER 557 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E557 general aviation airfoil Max thickness 16% at 30.2% chord Max camber 3.7% at 60.8% chord Max Cl/Cd 122.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca633618-il) NACA 63(3)-618		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(3)-618 airfoil Max thickness 18% at 34.7% chord Max camber 3.3% at 50% chord Max Cl/Cd 122.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n2h15-il) NACA 2-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 4.5% at 40% chord Max Cl/Cd 122.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq3512-il) HQ 3.5/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 122 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database