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NACA 1-H-15 AIRFOIL (n1h15-il)

NACA 1-H-15 AIRFOIL - NACA 1-H-15 rotorcraft airfoil


Airfoil n1h15-il
Details Dat file Parser  
(n1h15-il) NACA 1-H-15 AIRFOIL
NACA 1-H-15 rotorcraft airfoil
Max thickness 14.7% at 40% chord.
Max camber 5.5% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA 1-H-15 AIRFOIL
       18.       18.

 0.0000000 0.0000000
 0.0125000 0.0243600
 0.0250000 0.0332200
 0.0500000 0.0469500
 0.0750000 0.0583800
 0.1000000 0.0682000
 0.1500000 0.0848500
 0.2000000 0.0986000
 0.2500000 0.1098500
 0.3000000 0.1186000
 0.4000000 0.1286000
 0.5000000 0.1276000
 0.6000000 0.1125000
 0.7000000 0.0812000
 0.8000000 0.0388000
 0.9000000 0.0048000
 0.9500000 0.0023500
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0137400
 0.0250000 -.0160700
 0.0500000 -.0177500
 0.0750000 -.0182200
 0.1000000 -.0185000
 0.1500000 -.0185500
 0.2000000 -.0185000
 0.2500000 -.0182500
 0.3000000 -.0183000
 0.4000000 -.0186000
 0.5000000 -.0192000
 0.6000000 -.0195000
 0.7000000 -.0191000
 0.8000000 -.0171000
 0.9000000 -.0125000
 0.9500000 -.0081500
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for NACA 1-H-15 AIRFOIL (n1h15-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n1h15-il50,000918.6 at α=13.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n1h15-il50,000512.6 at α=15.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n1h15-il100,000920.3 at α=14°Mach=0 Ncrit=9Xfoil predictionDetails
   n1h15-il100,000519.2 at α=10.75°Mach=0 Ncrit=5Xfoil predictionDetails
   n1h15-il200,000929 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n1h15-il200,000531.1 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n1h15-il500,0009103.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   n1h15-il500,0005102.2 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   n1h15-il1,000,0009150.2 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n1h15-il1,000,0005133.2 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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