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.

(fx69pr281-il) FX 69-PR-281		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 69-PR-281 airfoil Max thickness 28.1% at 22.2% chord Max camber 5.6% at 50% chord Source UIUC Airfoil Coordinates Database
(ah95160-il) AH 95-160		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 95-160 airfoil Max thickness 16% at 38.9% chord Max camber 5.6% at 44.6% chord Source UIUC Airfoil Coordinates Database
(ah94145-il) AH 94-145		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 94-145 airfoil Max thickness 14.6% at 38.9% chord Max camber 5.6% at 44.6% chord Source UIUC Airfoil Coordinates Database
(usa29-il) USA 29 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-29 airfoil Max thickness 13.2% at 29.7% chord Max camber 5.5% at 39.7% chord Source UIUC Airfoil Coordinates Database
(n1h15-il) NACA 1-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 5.5% at 40% chord Source UIUC Airfoil Coordinates Database

(mh115-il) MH 115 11.06%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 115 for a propeller for ultralight Max thickness 11.1% at 29.8% chord Max camber 5.5% at 46% chord Source UIUC Airfoil Coordinates Database
(la203a-il) DOUGLAS LA203A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Douglas/Liebeck LA203A high lift airfoil Max thickness 15.7% at 34.3% chord Max camber 5.5% at 46% chord Source UIUC Airfoil Coordinates Database
(goe92-il) GOE 92 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 92 airfoil Max thickness 8.8% at 30% chord Max camber 5.5% at 30% chord Source UIUC Airfoil Coordinates Database
(goe610bm-il) GOE 610-B MOD. AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 610-B MOD airfoil Max thickness 7.7% at 30% chord Max camber 5.5% at 40% chord Source UIUC Airfoil Coordinates Database
(goe498-il) GOE 498 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 498 airfoil Max thickness 15.9% at 29.4% chord Max camber 5.5% at 49.4% chord Source UIUC Airfoil Coordinates Database