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.

(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
(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
(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
(fx78pk188-il) FX 78-PK-188/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 78-PK-188/20 variable geometry airfoil Max thickness 18.8% at 43.5% chord Max camber 2.4% at 50% chord Source UIUC Airfoil Coordinates Database
(goe622-il) GOE 622 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 622 airfoil Max thickness 8% at 30% chord Max camber 2.4% at 40% chord Source UIUC Airfoil Coordinates Database

(goe795-il) GOE 795 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 795 airfoil Max thickness 8% at 30.9% chord Max camber 2.4% at 43.5% chord Source UIUC Airfoil Coordinates Database
(goe795sm-il) GOE 795 smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 795 airfoil (smoothed) Max thickness 8% at 30.9% chord Max camber 2.4% at 43.5% chord Source UIUC Airfoil Coordinates Database
(ls413-il) NASA/LANGLEY LS(1)-0413 (GA(W)-2) 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)-0413 (GA(W)-2) general aviation airfoil Max thickness 12.9% at 37.5% chord Max camber 2.4% at 65% chord Source UIUC Airfoil Coordinates Database
(ls417-il) NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Whitcomb LS(1)-0417 (GA(W)-1) general aviation airfoil Max thickness 17% at 40% chord Max camber 2.4% at 65% 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