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NACA M27 AIRFOIL (m27-il)

NACA M27 AIRFOIL - NACA/Munk M-27 airfoil


Airfoil m27-il
Details Dat file Parser  
(m27-il) NACA M27 AIRFOIL
NACA/Munk M-27 airfoil
Max thickness 12% at 30.1% chord.
Max camber 8.4% at 30.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M27 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0126100 0.0244500
 0.0251600 0.0382900
 0.0502600 0.0598800
 0.0753300 0.0774800
 0.1004000 0.0920700
 0.1504900 0.1143500
 0.2005600 0.1297400
 0.3006200 0.1434100
 0.4006000 0.1393800
 0.5005300 0.1228500
 0.6004200 0.0988200
 0.7003100 0.0712900
 0.8001900 0.0436600
 0.9000800 0.0195300
 0.9500400 0.0101100
 1.0000000 0.0026000

 0.0000000 0.0000000
 0.0124500 -.0118500
 0.0249500 -.0118100
 0.0499700 -.0080100
 0.0749900 -.0025200
 0.1000100 0.0028700
 0.1500500 0.0118500
 0.2000800 0.0186400
 0.3001000 0.0239100
 0.4000900 0.0205800
 0.5000500 0.0115500
 0.6000000 0.0005200
 0.6999600 -.0093100
 0.7999300 -.0151400
 0.8999400 -.0137700
 0.9499600 -.0094800
 1.0000000 -.0026000
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Lednicer format dat file
Selig format dat file

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Polars for NACA M27 AIRFOIL (m27-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m27-il50,00094.7 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m27-il50,00059.6 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m27-il100,00099 at α=0.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m27-il100,000541.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m27-il200,000962.8 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m27-il200,000570.1 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m27-il500,0009105.5 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m27-il500,0005105 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m27-il1,000,0009135.9 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m27-il1,000,0005126.2 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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