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
(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
(e330-il) EPPLER 330 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E330 flying wing airfoil Max thickness 11% at 29.2% chord Max camber 2.1% at 16.9% chord Source UIUC Airfoil Coordinates Database
(e817-il) EPPLER 817 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E817 hydrofoil Max thickness 11% at 32.9% chord Max camber 2.9% at 66.7% chord Source UIUC Airfoil Coordinates Database

(fx63110-il) FX 63-110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-110 airfoil Max thickness 11% at 30.8% chord Max camber 4.3% at 50% chord Source UIUC Airfoil Coordinates Database
(giiia-il) GIII BL0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 11% at 39.7% chord Max camber 0.7% at 14.7% chord Source UIUC Airfoil Coordinates Database
(goe07k-il) GOE 7K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 7K airfoil Max thickness 11% at 50% chord Max camber 4.5% at 50% chord Source UIUC Airfoil Coordinates Database
(goe436-il) GOE 436 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 436 airfoil Max thickness 11% at 30% chord Max camber 3.8% at 30% chord Source UIUC Airfoil Coordinates Database
(goe438-il) GOE 438 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 438 airfoil Max thickness 11% at 29.8% chord Max camber 3.8% at 39.8% chord Source UIUC Airfoil Coordinates Database