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NACA M18 (nacam18-il)

NACA M18 - NACA M18 airfoil


Airfoil nacam18-il
Details Dat file Parser  
(nacam18-il) NACA M18
NACA M18 airfoil
Max thickness 12% at 30% chord.
Max camber 4.1% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA M18
1.0000     0.0295
0.9500     0.0366
0.9000     0.0445
0.8000     0.0623
0.7000     0.0809
0.6000     0.0982
0.5000     0.1133
0.4000     0.1226
0.3000     0.1242
0.2000     0.1148
0.1500     0.1047
0.1000     0.0894
0.0750     0.0799
0.0500     0.0678
0.0250     0.0525
0.0125     0.0425
0.0000     0.0220
0.0125     0.0056
0.0250     0.0025
0.0500     0.0003
0.0750     0.0000
0.1000     0.0003
0.1500     0.0017
0.2000     0.0031
0.3000     0.0046
0.4000     0.0041
0.5000     0.0019
0.6000     0.0003
0.7000     0.0005
0.8000     0.0040
0.9000     0.0117
0.9500     0.0175
1.0000     0.0251
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Lednicer format dat file
Selig format dat file

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Polars for NACA M18 (nacam18-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   nacam18-il50,000910.2 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam18-il50,000526.2 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam18-il100,000947.9 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam18-il100,000550.8 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam18-il200,000971.7 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam18-il200,000572.3 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam18-il500,0009102.6 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam18-il500,000599.2 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   nacam18-il1,000,0009125.1 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   nacam18-il1,000,0005114 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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