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NACA M2 (nacam2-il)

NACA M2 - NACA M2 airfoil


Airfoil nacam2-il
Details Dat file Parser  
(nacam2-il) NACA M2
NACA M2 airfoil
Max thickness 8.1% 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 M2
1.0000     0.0020
0.9500     0.0069
0.9000     0.0115
0.8000     0.0199
0.7000     0.0271
0.6000     0.0330
0.5000     0.0374
0.4000     0.0400
0.3000     0.0403
0.2000     0.0378
0.1500     0.0349
0.1000     0.0305
0.0750     0.0274
0.0500     0.0233
0.0250     0.0174
0.0125     0.0130
0.0000     0.0000
0.0125     -0.0130
0.0250     -0.0174
0.0500     -0.0233
0.0750     -0.0274
0.1000     -0.0305
0.1500     -0.0349
0.2000     -0.0378
0.3000     -0.0403
0.4000     -0.0400
0.5000     -0.0374
0.6000     -0.0330
0.7000     -0.0271
0.8000     -0.0199
0.9000     -0.0115
0.9500     -0.0069
1.0000     -0.0020
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Lednicer format dat file
Selig format dat file

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Polars for NACA M2 (nacam2-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   nacam2-il50,000925.5 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam2-il50,000523.6 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam2-il100,000933.2 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam2-il100,000527.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam2-il200,000938.6 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam2-il200,000536.1 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam2-il500,000944.5 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam2-il500,000554.4 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam2-il1,000,000960.3 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam2-il1,000,000570.5 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
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