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.

(goe723-il) GOE 723 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 723 airfoil Max thickness 11.6% at 29.7% chord Max camber 4.5% at 49.7% chord Max Cl/Cd 79.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe269-il) GOE 269 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 269 airfoil Max thickness 6.6% at 29.9% chord Max camber 5% at 39.9% chord Max Cl/Cd 79.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe264-il) GOE 264 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 264 airfoil Max thickness 6.4% at 20.2% chord Max camber 5.7% at 28.9% chord Max Cl/Cd 79.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(cr1-il) CURTISS CR-1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Curtiss CR-1 general aviation airfoil Max thickness 12.2% at 24% chord Max camber 4.7% at 42% chord Max Cl/Cd 79.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe365-il) GOE 365 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 365 airfoil Max thickness 11.7% at 29.9% chord Max camber 5.1% at 39.9% chord Max Cl/Cd 79.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(n11h9-il) NACA 11-H-09 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 11-H-9 rotorcraft airfoil Max thickness 9% at 40.2% chord Max camber 4.5% at 30% chord Max Cl/Cd 79.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe379-il) GOE 379 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 379 airfoil Max thickness 6.5% at 30% chord Max camber 5.2% at 40% chord Max Cl/Cd 79.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe397-il) GOE 397 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 397 airfoil Max thickness 5.1% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 79.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx60100sm-il) FX60-100 10.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-100 airfoil (smoothed) Max thickness 10% at 27.9% chord Max camber 3.5% at 56.5% chord Max Cl/Cd 79.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe300-il) GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 300 (Friedrichshafen G20) airfoil Max thickness 8.4% at 30% chord Max camber 6.7% at 30% chord Max Cl/Cd 79.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database