Airfoil Tools
Search 1638 airfoils

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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.

(nl722362-il) NLR-7223-62 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7223-62 transonic rotorcraft airfoil Max thickness 8.6% at 38% chord Max camber 1.3% at 21.6% chord Source UIUC Airfoil Coordinates Database
(nlf0115-il) NLF(1)-0115		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers-Selig-Maughmer NLF(1)-0115 natural laminar flow airfoil Max thickness 15% at 44.1% chord Max camber 1.8% at 30% chord Source UIUC Airfoil Coordinates Database
(nlf0215f-il) NASA/LANGLEY NLF(1)-0215F AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers NLF(1)-0215F natural laminar flow airfoil Max thickness 15% at 37.7% chord Max camber 4% at 42.3% chord Source UIUC Airfoil Coordinates Database
(nlf1015-il) NASA NLF1015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers-Maughmer NLF(1)-1015 natural laminar flow airfoil Max thickness 15% at 39.8% chord Max camber 4.3% at 62.8% chord Source UIUC Airfoil Coordinates Database
(nlf414f-il) NASA/LANGLEY NLF 0414F AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Viken NLF(1)-0414F natural laminar flow airfoil Max thickness 14.2% at 46.6% chord Max camber 2.4% at 53.7% chord Source UIUC Airfoil Coordinates Database

(nlf415-il) NASA/LANGLEY NLF(2)-0415 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley-DFVLR/Somers(NASA)-Horstmann(DFVLR) NLF(2)-0415 natural laminar flow airfoil Max thickness 15% at 47.1% chord Max camber 3% at 71.4% chord Source UIUC Airfoil Coordinates Database
(nlf416-il) NASA/LANGLEY NLF(1)-0416 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers NLF(1)-0416 natural laminar flow airfoil Max thickness 15.9% at 30.4% chord Max camber 2.5% at 34.8% chord Source UIUC Airfoil Coordinates Database
(nlr1t-il) NLR-1T AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell/NASA/NLR NLR-1T rotorcraft airfoil Max thickness 8.7% at 38.3% chord Max camber 1.3% at 22.3% chord Source UIUC Airfoil Coordinates Database
(nlr7301-il) NLR-7301 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7301 transonic airfoil Max thickness 16.5% at 35% chord Max camber 1.7% at 75% chord Source UIUC Airfoil Coordinates Database
(nn7mk20-il) NN7 MK20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NN7 MK20 airfoil Max thickness 16.9% at 37.1% chord Max camber 3% at 59.8% chord Source UIUC Airfoil Coordinates Database