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NACA M3 (nacam3-il)

NACA M3 - NACA M3 airfoil


Airfoil nacam3-il
Details Dat file Parser  
(nacam3-il) NACA M3
NACA M3 airfoil
Max thickness 11.9% at 30% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA M3
1.0000     0.0020
0.9500     0.0093
0.9000     0.0162
0.8000     0.0288
0.7000     0.0396
0.6000     0.0485
0.5000     0.0550
0.4000     0.0589
0.3000     0.0595
0.2000     0.0557
0.1500     0.0514
0.1000     0.0447
0.0750     0.0400
0.0500     0.0339
0.0250     0.0251
0.0125     0.0186
0.0000     0.0000
0.0125     -0.0186
0.0250     -0.0251
0.0500     -0.0339
0.0750     -0.0400
0.1000     -0.0447
0.1500     -0.0514
0.2000     -0.0557
0.3000     -0.0595
0.4000     -0.0589
0.5000     -0.0550
0.6000     -0.0485
0.7000     -0.0396
0.8000     -0.0288
0.9000     -0.0162
0.9500     -0.0093
1.0000     -0.0020
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Lednicer format dat file
Selig format dat file

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Polars for NACA M3 (nacam3-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   nacam3-il50,000927.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam3-il50,000526.6 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam3-il100,000937.9 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam3-il100,000534.6 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam3-il200,000945.8 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam3-il200,000542.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam3-il500,000954.9 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam3-il500,000556.8 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam3-il1,000,000966.9 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam3-il1,000,000569.5 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
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