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.

(goe513-il) GOE 513 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 513 airfoil Max thickness 16.6% at 29.8% chord Max camber 5.2% at 39.8% chord Max Cl/Cd 43 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe549-il) GOE 549 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 549 airfoil Max thickness 13.9% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 43 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca65210-il) NACA 65-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 43 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca633218-il) NACA 63(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(3)-218 airfoil Max thickness 18% at 34.9% chord Max camber 1.1% at 24.9% chord Max Cl/Cd 43 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe703-il) GOE 703 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 703 airfoil Max thickness 19.4% at 30% chord Max camber 2.3% at 30% chord Max Cl/Cd 43 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(naca1412-il) NACA 1412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1412 airfoil Max thickness 12% at 29.9% chord Max camber 1% at 40% chord Max Cl/Cd 43 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(eh1090-il) EH 1.0/9.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.0/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 1% at 25.9% chord Max Cl/Cd 43 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(cast102-il) CAST 10-2/DOA 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord Max Cl/Cd 43 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(r140sm-il) R140 12.04% (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	R140 Quickee 500 airfoil (smoothed) Max thickness 12% at 39.3% chord Max camber 0.4% at 39.3% chord Max Cl/Cd 43 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e642-il) EPPLER 642 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E642 sailplane airfoil Max thickness 15.1% at 39.4% chord Max camber 3% at 39.4% chord Max Cl/Cd 43 at Re# 100,000 Source UIUC Airfoil Coordinates Database