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NACA M17 AIRFOIL (m17-il)

NACA M17 AIRFOIL - NACA/Munk M-17 airfoil


Airfoil m17-il
Details Dat file Parser  
(m17-il) NACA M17 AIRFOIL
NACA/Munk M-17 airfoil
Max thickness 8.1% at 40% chord.
Max camber 4.1% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M17 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125300 0.0155700
 0.0250500 0.0234500
 0.0500700 0.0358000
 0.0750900 0.0456500
 0.1001100 0.0535900
 0.1501300 0.0650900
 0.2001500 0.0731900
 0.3001700 0.0814800
 0.4001600 0.0798800
 0.5001500 0.0710700
 0.6001200 0.0576700
 0.7000901 0.0424600
 0.8000600 0.0268600
 0.9000300 0.0129500
 0.9500100 0.0070500
 1.0000000 0.0020500

 0.0000000 0.0000000
 0.0124800 -.0104300
 0.0249800 -.0115500
 0.0499800 -.0110000
 0.0749800 -.0094500
 0.0999800 -.0075000
 0.1499900 -.0041100
 0.2000000 -.0014100
 0.3000000 0.0007800
 0.4000000 -.0009200
 0.4999900 -.0046200
 0.5999800 -.0096300
 0.6999700 -.0123300
 0.7999700 -.0130400
 0.8999800 -.0101400
 0.9499900 -.0067500
 1.0000000 -.0020500
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Lednicer format dat file
Selig format dat file

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Polars for NACA M17 AIRFOIL (m17-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m17-il50,000935.7 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m17-il50,000535.6 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m17-il100,000955.2 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m17-il100,000555.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m17-il200,000975.3 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   m17-il200,000574.2 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m17-il500,0009102.4 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m17-il500,000598.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m17-il1,000,0009122.3 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m17-il1,000,0005114.8 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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