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.

(fx711525-il) FX 71-L-150/25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 71-L-150/25 airfoil Max thickness 15% at 33.9% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(v43015-il) BOEING VERTOL V43015-2.48 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V43015-2.48 rotorcraft airfoil Max thickness 15% at 30% chord Max camber 3.7% at 15% chord Source UIUC Airfoil Coordinates Database
(n63215-il) NACA 63-215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(mb253515sm-il) MB253515 15.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Mike Bame MB253515 low Reynolds number airfoil Max thickness 15% at 35% chord Max camber 2.5% at 37.5% chord Source UIUC Airfoil Coordinates Database
(mh91-il) MH 91 14.98%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 91 parafoil Max thickness 15% at 27.3% chord Max camber 1.4% at 18.7% chord Source UIUC Airfoil Coordinates Database

(n63015a-il) NACA 63-015A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-015A airfoil Max thickness 15% at 35% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca4415-il) NACA 4415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4415 airfoil Max thickness 15% at 30.9% chord Max camber 4% at 40.2% chord Source UIUC Airfoil Coordinates Database
(e678-il) EPPLER 678 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E678 sailplane airfoil Max thickness 15.1% at 39.8% chord Max camber 5.1% at 53.7% chord Source UIUC Airfoil Coordinates Database
(e642-il) EPPLER 642 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E642 sailplane airfoil Max thickness 15.1% at 39.4% chord Max camber 3% at 39.4% 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