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.

(doa5-il) DORNIER A-5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dornier A-5 airfoil (reconstruction) (DO 228 wing) Max thickness 16.2% at 40.1% chord Max camber 2.5% at 76% chord Source UIUC Airfoil Coordinates Database
(dormoy-il) Dormoy		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dormoy airfoil Max thickness 9% at 30% chord Max camber 2.9% at 40% chord Source UIUC Airfoil Coordinates Database
(drgnfly-il) DRAGONFLY CANARD		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dragonfly Canard airfoil Max thickness 19.3% at 37.6% chord Max camber 6.6% at 40.9% chord Source UIUC Airfoil Coordinates Database
(dsma523a-il) DSMA-523A 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 sharp trailing edge Max thickness 11% at 36% chord Max camber 2.3% at 82% 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

(du06-w-200-dt) DU 06-W-200 VAWT airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	DU 06-W-200 airfoil for Small Vertical Axis Wind Turbines (VAWT) Max thickness 19.8% at 31.1% chord Max camber 0.5% at 84.6% chord Source TU Delft
(du84132v-il) DELFT DU84-132V3 AIRFOIL (MEASURED)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Airfoil measured from an ASW22 wing Max thickness 13.6% at 33.9% chord Max camber 3.1% at 45.3% chord Source UIUC Airfoil Coordinates Database
(du8608418-il) DU86-084/18 8.44%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Deflt University DU 86-084/18 low Reynolds number airfoil Max thickness 8.5% at 36.9% chord Max camber 1% at 45.8% chord Source UIUC Airfoil Coordinates Database
(du861372-il) DU 86-137/25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Delft University DU 86-137/25 Airfoil Max thickness 13.6% at 41.6% chord Max camber 0.3% at 1.6% chord Source UIUC Airfoil Coordinates Database
(e1098-il) EPPLER 1098 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1098 general aviation airfoil Max thickness 18.9% at 36.6% chord Max camber 3.7% at 54.5% chord Source UIUC Airfoil Coordinates Database