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.

(s4233-il) S4233-136-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4233 low Reynolds number airfoil Max thickness 13.6% at 34.9% chord Max camber 2.7% at 48.8% chord Source UIUC Airfoil Coordinates Database
(goe14k-il) GOE 14K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 14K airfoil Max thickness 12% at 50% chord Max camber 2.7% at 50% chord Source UIUC Airfoil Coordinates Database
(goe564-il) GOE 564 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 564 airfoil Max thickness 8.2% at 30% chord Max camber 2.7% at 40% chord Source UIUC Airfoil Coordinates Database
(goe344-il) GOE 344 (PFALZ 71) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 344 (Pfalz 71) airfoil Max thickness 7.2% at 19.9% chord Max camber 2.7% at 39.9% chord Source UIUC Airfoil Coordinates Database
(l188tip-il) LOCKHEED L-188 TIP AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed L-188/P-3 tip airfoil NACA 0012 -1.10 40/1.051 Cli=.4 a=.8 Max thickness 12% at 41.3% chord Max camber 2.7% at 51.7% chord Source UIUC Airfoil Coordinates Database

(cp-060-050-gn) Cambered plate C=6% T=5% R=2.11		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=6% Wall thickness=5% Radius=2.113 Max thickness 10.8% at 6.3% chord Max camber 2.7% at 52.1% chord Source Generated
(mh18-il) MH 18 11.16%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 18 for F3D Pylon Racing Max thickness 11.1% at 36.8% chord Max camber 2.7% at 42.1% chord Source UIUC Airfoil Coordinates Database
(kc135winglet-il) KC-135 Winglet (supercritical Whitcomb)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 winglet airfoil designed by Richard T. Whitcomb Max thickness 8% at 40% chord Max camber 2.7% at 65% chord Source UIUC Airfoil Coordinates Database
(goe11k-il) GOE 11K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 11K airfoil Max thickness 7.5% at 50% chord Max camber 2.7% at 60% chord Source UIUC Airfoil Coordinates Database
(e201-il) E201 (11.88%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E201 low Reynolds number airfoil Max thickness 11.9% at 30.8% chord Max camber 2.6% at 49.4% chord Source UIUC Airfoil Coordinates Database