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.

(naca23012-il) NACA 23012 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23012 airfoil Max thickness 12% at 29.8% chord Max camber 1.8% at 12.7% chord Source UIUC Airfoil Coordinates Database
(mh42-il) MH 42 8.94%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 42 low Reynolds number airfoil Max thickness 8.9% at 31.3% chord Max camber 1.8% at 36.3% chord Source UIUC Airfoil Coordinates Database
(s4094-il) S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for micro RC soaring. Used on the E-flite UMX ASK-21 scale RC sailplane. Max thickness 9.9% at 29.1% chord Max camber 1.8% at 33.6% chord Source UIUC Airfoil Coordinates Database
(c141e-il) LOCKHEED C-141 BL761.11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10.5% at 40.2% chord Max camber 1.8% at 50% chord Source UIUC Airfoil Coordinates Database
(s822-nr) NREL's S822 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S822 tip 16.0% Dia=2 to 10 m Re=6.0E+5 Clmax(S)=1.00 Clmax(R)=0.98 Restrained max lift coef Max thickness 16% at 39.2% chord Max camber 1.8% at 59.5% chord Source NWTC National WInd Technology Center

(ms313-il) NASA/LANGLEY MS(1)-0313 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley MS(1)-0313 general aviation airfoil (buggy Max thickness 13.1% at 37.5% chord Max camber 1.8% at 67.5% chord Source UIUC Airfoil Coordinates Database
(ag12-il) AG12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG12 airfoil Max thickness 6.2% at 20.8% chord Max camber 1.8% at 42.8% chord Source UIUC Airfoil Coordinates Database
(mh22-il) MH 22 7.2%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 22 for F3D Pylon Racing Max thickness 7.2% at 27% chord Max camber 1.8% at 37% chord Source UIUC Airfoil Coordinates Database
(ag09-il) AG09		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG09 airfoil Max thickness 4.9% at 17.4% chord Max camber 1.8% at 34.1% chord Source UIUC Airfoil Coordinates Database
(e850-il) EPPLER E850 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E850 propeller airfoil Max thickness 8% at 36.6% chord Max camber 1.8% at 71% chord Source UIUC Airfoil Coordinates Database