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.

(goe367-il) GOE 367 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 367 airfoil Max thickness 16.3% at 29.7% chord Max camber 4.6% at 39.7% chord Source UIUC Airfoil Coordinates Database
(goe371-il) GOE 371 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 371 airfoil Max thickness 7% at 29.9% chord Max camber 4.6% at 39.9% chord Source UIUC Airfoil Coordinates Database
(goe413-il) GOE 413 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 413 airfoil Max thickness 16.4% at 30% chord Max camber 4.6% at 40% chord Source UIUC Airfoil Coordinates Database
(goe426-il) GOE 426 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 426 airfoil Max thickness 13.6% at 30% chord Max camber 4.6% at 40% chord Source UIUC Airfoil Coordinates Database
(isa961-il) I.S.A. 961		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 961 airfoil Max thickness 9.3% at 20% chord Max camber 4.6% at 40% chord Source UIUC Airfoil Coordinates Database

(isa962-il) I.S.A. 962		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 962 airfoil Max thickness 9.6% at 20% chord Max camber 4.6% at 40% chord Source UIUC Airfoil Coordinates Database
(n6h10-il) NACA 6-H-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6-H-10 rotorcraft airfoil Max thickness 10% at 40% chord Max camber 4.6% at 40% chord Source UIUC Airfoil Coordinates Database
(raf6-il) RAF 6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-6 airfoil Max thickness 10% at 30% chord Max camber 4.6% at 30% chord Source UIUC Airfoil Coordinates Database
(rhodesg34-il) Rhode St. Genese 34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rhode St. Genese 34 airfoil Max thickness 14.1% at 30% chord Max camber 4.6% at 40% chord Source UIUC Airfoil Coordinates Database
(s1020-il) Ornithopter airfoil.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1020 ornithopter airfoil Max thickness 15.1% at 33.8% chord Max camber 4.6% at 57% chord Source UIUC Airfoil Coordinates Database