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Airfoil database list (N).

NACA 6-H-10 AIRFOIL to NACA 0015

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(n6h10-il) NACA 6-H-10 AIRFOIL

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NACA 6-H-10 AIRFOILNACA 6-H-10 rotorcraft airfoil
Max thickness 10% at 40% chord
Max camber 4.6% at 40% chord
Source UIUC Airfoil Coordinates Database

(n6h15-il) NACA 6-H-15 AIRFOIL

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NACA 6-H-15 AIRFOILNACA 6-H-15 rotorcraft airfoil
Max thickness 15.6% at 40% chord
Max camber 4.5% at 40% chord
Source UIUC Airfoil Coordinates Database

(n6h20-il) NACA 6-H-20 AIRFOIL

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NACA 6-H-20 AIRFOILNACA 6-H-20 rotorcraft airfoil
Max thickness 20% at 40% chord
Max camber 6.1% at 40% chord
Source UIUC Airfoil Coordinates Database

(n8h12-il) NACA 8-H-12 AIRFOIL

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NACA 8-H-12 AIRFOILNACA 8-H-12 rotorcraft airfoil
Max thickness 12% at 30% chord
Max camber 3.5% at 30% chord
Source UIUC Airfoil Coordinates Database

(n9-il) N-9

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N-9N-9 airfoil
Max thickness 8.5% at 30% chord
Max camber 2.7% at 40% chord
Source UIUC Airfoil Coordinates Database

(naca0006-il) NACA 0006

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NACA 0006NACA 0006 airfoil
Max thickness 6% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca0008-il) NACA 0008

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NACA 0008NACA 0008 airfoil
Max thickness 8% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca000834-il) NACA 0008-34

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NACA 0008-34NACA 0008-34 airfoil
Max thickness 8% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca0010-il) NACA 0010

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NACA 0010NACA 0010 airfoil
Max thickness 10% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001034-il) NACA 0010-34

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NACA 0010-34NACA 0010-34 airfoil
Max thickness 10% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001034a08cli02-il) NACA 0010-34 a=0.8 c(li)=0.2

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NACA 0010-34 a=0.8 c(li)=0.2NACA 0010-34 a=0.8 c(li)=0.2 airfoil
Max thickness 10% at 40% chord
Max camber 1.3% at 50% chord
Source UIUC Airfoil Coordinates Database

(naca001035-il) NACA 0010-35

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NACA 0010-35NACA 0010-35 airfoil
Max thickness 10% at 50% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001064-il) NACA 0010-64

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NACA 0010-64NACA 0010-64 airfoil
Max thickness 10% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001065-il) NACA 0010-65

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NACA 0010-65NACA 0010-65 airfoil
Max thickness 10% at 50% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001066-il) NACA 0010-66

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NACA 0010-66NACA 0010-66 airfoil
Max thickness 10% at 60% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001234-il) NACA 0012-34

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NACA 0012-34NACA 0012-34 airfoil
Max thickness 12% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001264-il) NACA 0012-64

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NACA 0012-64NACA 0012-64 airfoil
Max thickness 12% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(naca001264a08cli02-il) NACA 0012-64 a=0.8 c(li)=0.2

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NACA 0012-64 a=0.8 c(li)=0.2NACA 0012-64 a=0.8 c(li)=0.2 airfoil
Max thickness 11% at 39.9% chord
Max camber 1.8% at 29.9% chord
Source UIUC Airfoil Coordinates Database

(naca0012h-sa) NACA0012H for VAWT from Sandia report SAND80-2114

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NACA0012H for VAWT from Sandia report SAND80-2114Modified Naca 0012 airfoil for Sandia VAWT tests
Max thickness 12.2% at 22.5% chord
Max camber 0% at 0% chord
Source Sandia National Laboratories

(naca0015-il) NACA 0015

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NACA 0015NACA 0015 airfoil
Max thickness 15% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
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