Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(goe101-il) GOE 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 101 airfoil Max thickness 6.9% at 30% chord Max camber 4% at 30% chord Max Cl/Cd 123.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh83-il) MH 83 13.29%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 83 for flying wings (hang glider) Max thickness 13.3% at 20.6% chord Max camber 4.5% at 32.6% chord Max Cl/Cd 123.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe498-il) GOE 498 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 498 airfoil Max thickness 15.9% at 29.4% chord Max camber 5.5% at 49.4% chord Max Cl/Cd 123.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e604-il) EPPLER 604 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E604 sailplane airfoil Max thickness 18.8% at 37.3% chord Max camber 3.4% at 42.3% chord Max Cl/Cd 123.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca643418-il) NACA 64(3)-418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(3)-418 airfoil Max thickness 17.9% at 34.8% chord Max camber 2.2% at 50% chord Max Cl/Cd 123.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe437-il) GOE 437 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 437 airfoil Max thickness 7.1% at 30% chord Max camber 4.8% at 40% chord Max Cl/Cd 123.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe439-il) GOE 439 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 439 airfoil Max thickness 7.9% at 30% chord Max camber 5.2% at 40% chord Max Cl/Cd 123.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(apex16-il) Apex 16 (normalized using XFOIL date021206)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela Apex 16 low Reynolds number transonic research airfoil Max thickness 12.9% at 38.6% chord Max camber 2.4% at 59.6% chord Max Cl/Cd 123.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx84w097-il) FX 84-W-097		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 84-W-097 airfoil for use on wind turbines (W) Max thickness 9.7% at 33.9% chord Max camber 2.8% at 37.1% chord Max Cl/Cd 123.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e559-il) EPPLER 559 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E559 general aviation airfoil Max thickness 16% at 27.2% chord Max camber 4.3% at 50.2% chord Max Cl/Cd 123.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database