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.

(hq17-il) HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Airfoil measured from an ASW22 wing Max thickness 15.2% at 42% chord Max camber 4.5% at 42% chord Source UIUC Airfoil Coordinates Database
(isa960-il) I.S.A. 960		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 960 airfoil Max thickness 9.5% at 30% chord Max camber 4.5% at 40% chord Source UIUC Airfoil Coordinates Database
(mh150-il) MH 150 23.89%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 150 for marine ruddershaft for torque reduction (schottel units) Max thickness 23.9% at 27.2% chord Max camber 4.5% at 53.8% chord Source UIUC Airfoil Coordinates Database
(mh83-il) MH 83 13.29%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 83 for flying wings (hang glider) Max thickness 13.3% at 20.6% chord Max camber 4.5% at 32.6% chord Source UIUC Airfoil Coordinates Database
(n11h9-il) NACA 11-H-09 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 11-H-9 rotorcraft airfoil Max thickness 9% at 40.2% chord Max camber 4.5% at 30% chord Source UIUC Airfoil Coordinates Database
(n2h15-il) NACA 2-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 4.5% at 40% chord Source UIUC Airfoil Coordinates Database
(n5h20-il) NACA 5-H-20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 5-H-20 rotorcraft airfoil Max thickness 19.9% at 40% chord Max camber 4.5% at 40% chord Source UIUC Airfoil Coordinates Database
(n6h15-il) NACA 6-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6-H-15 rotorcraft airfoil Max thickness 15.6% at 40% chord Max camber 4.5% at 40% chord Source UIUC Airfoil Coordinates Database
(s4320-il) S4320		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4320 low Reynolds number airfoil Max thickness 9.4% at 26.8% chord Max camber 4.5% at 40.2% chord Source UIUC Airfoil Coordinates Database
(usa41-il) USA 41 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-41 airfoil Max thickness 6.6% at 30% chord Max camber 4.5% at 40% chord Source UIUC Airfoil Coordinates Database

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