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NACA M25 AIRFOIL (m25-il)

NACA M25 AIRFOIL - NACA/Munk M-25 airfoil


Airfoil m25-il
Details Dat file Parser  
(m25-il) NACA M25 AIRFOIL
NACA/Munk M-25 airfoil
Max thickness 6.3% at 30% chord.
Max camber 8.2% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
NACA M25 AIRFOIL
       17.       17.

 0.0000000 0.0000000
 0.0125100 0.0161000
 0.0250100 0.0256900
 0.0500200 0.0436800
 0.0750200 0.0571700
 0.1000200 0.0692600
 0.1500300 0.0884500
 0.2000400 0.1021300
 0.3000400 0.1137000
 0.4000400 0.1099600
 0.5000300 0.0953200
 0.6000300 0.0746900
 0.7000200 0.0516500
 0.8000100 0.0296200
 0.9000000 0.0119900
 0.9500000 0.0060700
 1.0000000 0.0022500

 0.0000000 0.0000000
 0.0125000 -.0058000
 0.0250000 -.0022100
 0.0500000 0.0060800
 0.0750100 0.0147700
 0.1000100 0.0223700
 0.1500100 0.0346500
 0.2000200 0.0436300
 0.3000200 0.0510000
 0.4000200 0.0475600
 0.5000100 0.0367200
 0.6000100 0.0226900
 0.7000000 0.0084500
 0.8000000 -.0022800
 0.9000000 -.0070100
 0.9500000 -.0059300
 1.0000000 -.0022500
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Lednicer format dat file
Selig format dat file

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Polars for NACA M25 AIRFOIL (m25-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m25-il50,00096.8 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m25-il50,000520.5 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   m25-il100,000953.9 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m25-il100,000554.3 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m25-il200,000978.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m25-il200,000578.5 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m25-il500,0009102.3 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m25-il500,000594.5 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   m25-il1,000,0009111.9 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   m25-il1,000,0005107.8 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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