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NASA/LANGLEY NLF(1)-0215F AIRFOIL to NPL AIRFOIL FROM ARC CP 1372

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(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
(npl9510-il) NPL 9510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9510 transonic airfoil Max thickness 11.1% at 32% chord Max camber 1.6% at 80% chord Source UIUC Airfoil Coordinates Database
(npl9615-il) NPL 9615 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9615 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord Source UIUC Airfoil Coordinates Database
(npl9626-il) NPL 9626 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9626 rotorcraft airfoil Max thickness 12.1% at 30.9% chord Max camber 0.7% at 30.9% chord Source UIUC Airfoil Coordinates Database
(npl9627-il) NPL 9627 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9627 rotorcraft airfoil Max thickness 12.2% at 31% chord Max camber 0.9% at 40.4% chord Source UIUC Airfoil Coordinates Database
(npl9660-il) NPL 9660 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9660 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord Source UIUC Airfoil Coordinates Database

(nplx-il) NPL AIRFOIL FROM ARC CP 1372		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL transonic airfoil FROM ARC CP 1372 Max thickness 10.7% at 35.8% chord Max camber 1.1% at 73.7% chord Source UIUC Airfoil Coordinates Database