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.

(l7769-il) LISSAMAN 7769 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lissaman 7769 human powered aircraft airfoil Max thickness 11% at 30% chord Max camber 4.4% at 30% chord Source UIUC Airfoil Coordinates Database
(lnv109a-il) LNV109A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Douglas/Liebeck LNV109A high lift airfoil Max thickness 13% at 23.5% chord Max camber 6% at 31.5% chord Source UIUC Airfoil Coordinates Database
(c141a-il) LOCKHEED C-141 BL0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 13% at 40.2% chord Max camber 1.1% at 64.5% chord Source UIUC Airfoil Coordinates Database
(c141b-il) LOCKHEED C-141 BL113.6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 12.6% at 40.2% chord Max camber 1.1% at 64.5% chord Source UIUC Airfoil Coordinates Database
(c141c-il) LOCKHEED C-141 BL426.57 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 11% at 40.2% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database

(c141d-il) LOCKHEED C-141 BL610.61 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10.8% at 40.2% chord Max camber 1.5% at 50% chord Source UIUC Airfoil Coordinates Database
(c141e-il) LOCKHEED C-141 BL761.11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10.5% at 40.2% chord Max camber 1.8% at 50% chord Source UIUC Airfoil Coordinates Database
(c141f-il) LOCKHEED C-141 BL958.89 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10% at 40.2% chord Max camber 2.3% at 45.1% chord Source UIUC Airfoil Coordinates Database
(c5a-il) LOCKHEED C-5A BL0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 13.1% at 40% chord Max camber 0.7% at 85% chord Source UIUC Airfoil Coordinates Database
(c5e-il) LOCKHEED C-5A BL1256 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 10.8% at 40% chord Max camber 1.4% at 30% chord Source UIUC Airfoil Coordinates Database