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.

(goe595-il) GOE 595 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 595 airfoil Max thickness 9.6% at 30% chord Max camber 3% at 40% chord Max Cl/Cd 97.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe620-il) GOE 620 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 620 airfoil Max thickness 17.5% at 30% chord Max camber 5.9% at 50% chord Max Cl/Cd 97.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(usa35-il) USA 35 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-35 airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord Max Cl/Cd 97.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe442-il) GOE 442 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 442 airfoil Max thickness 7.7% at 19.9% chord Max camber 4.3% at 39.9% chord Max Cl/Cd 97.6 at Re# 500,000 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 97.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe276-il) GOE 276 (DAIMLER VII) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 276 (DAIMLER VII) airfoil Max thickness 7.3% at 30% chord Max camber 4% at 30% chord Max Cl/Cd 97.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe624-il) GOE 624 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 624 airfoil Max thickness 16% at 30% chord Max camber 5.2% at 40% chord Max Cl/Cd 97.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe449-il) GOE 449 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 449 airfoil Max thickness 17% at 30% chord Max camber 5.4% at 40% chord Max Cl/Cd 97.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca747a415-il) NACA 747A415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord Max Cl/Cd 97.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe366-il) GOE 366 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 366 airfoil Max thickness 13.1% at 29.8% chord Max camber 7.2% at 39.8% chord Max Cl/Cd 97.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database