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.

(e1210-il) EPPLER 1210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1210 general aviation airfoil Max thickness 15.9% at 21.1% chord Max camber 5.2% at 33.3% 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
(goe502-il) GOE 502 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 502 airfoil Max thickness 15.9% at 29.3% chord Max camber 6.1% at 49.4% chord Source UIUC Airfoil Coordinates Database
(la5055-il) LIEBECK LA5055 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Liebeck high lift airfoil Max thickness 15.9% at 35% chord Max camber 5.9% at 40% chord Source UIUC Airfoil Coordinates Database
(nlf416-il) NASA/LANGLEY NLF(1)-0416 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers NLF(1)-0416 natural laminar flow airfoil Max thickness 15.9% at 30.4% chord Max camber 2.5% at 34.8% 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
(as5046-il) AS5046 (16%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AS5046 airfoil Ashok Gopalarathnam/Selig 16% airfoil Max thickness 16% at 37.6% chord Max camber 0.7% at 77.4% chord Source UIUC Airfoil Coordinates Database
(august160-il) AUGUST 160		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AUGUST 160 airfoil Max thickness 16% at 25% chord Max camber 5.4% at 25% chord Source UIUC Airfoil Coordinates Database
(e432-il) EPPLER 432 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E432 sailplane airfoil Max thickness 16% at 37.4% chord Max camber 4.5% at 37.4% chord Source UIUC Airfoil Coordinates Database
(e555-il) EPPLER 555 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E555 general aviation airfoil Max thickness 16% at 31.9% chord Max camber 2.6% at 67.4% chord Source UIUC Airfoil Coordinates Database