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.

(rae5212-il) RAE(NPL) 5212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE(NPL) 5212 transonic airfoil Max thickness 11.9% at 35.5% chord Max camber 1.8% at 69.1% chord Source UIUC Airfoil Coordinates Database
(e325-il) EPPLER 325 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E325 flying wing airfoil Max thickness 12.6% at 34.3% chord Max camber 1.8% at 16.3% chord Source UIUC Airfoil Coordinates Database
(ys915-il) YS-915		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	YS915 hydrofoil (Shen / Eppler) Max thickness 9.1% at 36.1% chord Max camber 1.8% at 65.6% 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
(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

(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
(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
(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
(s816-nr) NREL's S816 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S816 primary 21.0% Dia=30 to 50 m Re=4.0E+6 Clmax(S)=1.20 Clmax(R)=1.17 Restrained max lift coef Max thickness 21% at 39% chord Max camber 1.8% at 67.6% chord Source NWTC National WInd Technology Center
(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