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.

(e203-il) E203 (13.64%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E203 low Reynolds number airfoil Max thickness 13.6% at 30.7% chord Max camber 2.3% at 54.1% chord Source UIUC Airfoil Coordinates Database
(dsma523b-il) DSMA-523B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	McDonnell/Douglas DSMA-523 transonic airfoil with blunt trailing edge Max thickness 11% at 36% chord Max camber 2.4% at 82% chord Source UIUC Airfoil Coordinates Database
(clarkys-il) CLARK YS AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YS airfoil Max thickness 11.7% at 30% chord Max camber 2.4% at 30% chord Source UIUC Airfoil Coordinates Database
(whitcomb-il) WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley Whitcomb integral supercritical airfoil Max thickness 11% at 35% chord Max camber 2.4% at 82.5% chord Source UIUC Airfoil Coordinates Database
(s808-nr) NREL's S808 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S808 root Max thickness 21% at 24.4% chord Max camber 2.4% at 72.9% chord Source NWTC National WInd Technology Center

(fx75vg166-il) FX 75-VG-166/22		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 75-VG-166/22 variable geometry airfoil Max thickness 16.7% at 43.5% chord Max camber 2.4% at 40.2% chord Source UIUC Airfoil Coordinates Database
(s835-nr) NREL's S835 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S835 root 21.0% Dia=1 to 3 m Re=2.5E+5 Clmax(S)=1.20 Clmax(R)=1.03 High max lift coef Max thickness 21% at 30.5% chord Max camber 2.4% at 78% chord Source NWTC National WInd Technology Center
(df102-il) DF102		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	David Fraser DF 102 low Reynolds number airfoil Max thickness 11% at 29.1% chord Max camber 2.4% at 43.5% chord Source UIUC Airfoil Coordinates Database
(ls421-il) NASA/LANGLEY LS(1)-0421 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0421 general aviation airfoil Max thickness 20.9% at 40% chord Max camber 2.4% at 65% chord Source UIUC Airfoil Coordinates Database
(defcnd3-il) DEFIANT CANARD BL145 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan DEFIANT canard BL145 airfoil Max thickness 11.5% at 28.6% chord Max camber 2.4% at 28.6% chord Source UIUC Airfoil Coordinates Database