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.

(ag36-il) AG36		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG36 airfoil Max thickness 8.2% at 27.9% chord Max camber 2.3% at 37% chord Max Cl/Cd 64.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe244-il) GOE 244 (MVA PR.4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 244 (MVA PR.4) airfoil Max thickness 17.7% at 19.6% chord Max camber 10% at 49.6% chord Max Cl/Cd 64.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe54-il) GOE 54 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 54 airfoil Max thickness 6.5% at 14.9% chord Max camber 3.5% at 19.9% chord Max Cl/Cd 64.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe563-il) GOE 563 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 563 airfoil Max thickness 8.9% at 29.8% chord Max camber 2.2% at 49.8% chord Max Cl/Cd 64.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(rg12-il) RG-12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 12 airfoil Max thickness 9.3% at 34.4% chord Max camber 1.4% at 34.4% chord Max Cl/Cd 64.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(sd8000-il) SD8000-089-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD8000 low Reynolds number airfoil Max thickness 8.9% at 29.4% chord Max camber 1.5% at 54% chord Max Cl/Cd 64.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe512-il) GOE 512 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 512 airfoil Max thickness 13.9% at 19.9% chord Max camber 5.6% at 29.9% chord Max Cl/Cd 64.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(oaf117-il) OAF117 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF117 Fenestron airfoil Max thickness 11.5% at 23.2% chord Max camber 2% at 46.9% chord Max Cl/Cd 64.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n2415-il) NACA 2415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2415 airfoil Max thickness 15% at 29.5% chord Max camber 2% at 39.6% chord Max Cl/Cd 64.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(eh3012-il) EH 3.0/12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 3.0/12 for tailless R/C aircraft Max thickness 12% at 30% chord Max camber 2.9% at 25% chord Max Cl/Cd 64.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database