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NACA M8 AIRFOIL (m8-il)

NACA M8 AIRFOIL - NACA/Munk M-8 airfoil


Airfoil m8-il
Details Dat file Parser  
(m8-il) NACA M8 AIRFOIL
NACA/Munk M-8 airfoil
Max thickness 11.7% at 15% chord.
Max camber 8% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M8 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125000 0.0350000
 0.0250000 0.0506000
 0.0500000 0.0718000
 0.0750000 0.0875000
 0.1000000 0.0995000
 0.1500000 0.1139000
 0.2000000 0.1212000
 0.2500000 0.1250000
 0.3000000 0.1241000
 0.4000000 0.1157000
 0.5000000 0.0989000
 0.6000000 0.0782000
 0.7000000 0.0544000
 0.8000000 0.0331000
 0.9000000 0.0133000
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0125000 -.0100000
 0.0250000 -.0129000
 0.0500000 -.0137000
 0.0750000 -.0120000
 0.1000000 -.0098000
 0.1500000 -.0033000
 0.2000000 0.0174000
 0.2500000 0.0298000
 0.3000000 0.0368000
 0.4000000 0.0443000
 0.5000000 0.0388000
 0.6000000 0.0311000
 0.7000000 0.0194000
 0.8000000 0.0083000
 0.9000000 0.0000000
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for NACA M8 AIRFOIL (m8-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m8-il50,00098.5 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m8-il50,000526.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m8-il100,000940.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m8-il100,000546.3 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   m8-il200,000960.2 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m8-il200,000562.1 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m8-il500,000983 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m8-il500,000579.6 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m8-il1,000,000996.6 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   m8-il1,000,000599.1 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
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