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M6 (85%) (m685-il)

M6 (85%) - NACA/Munk M6 (85%)


Airfoil m685-il
Details Dat file Parser  
(m685-il) M6 (85%)
NACA/Munk M6 (85%)
Max thickness 10.2% at 30% chord.
Max camber 1.9% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
M6 (85%)     
1       0
0.95    0.0068
0.9     0.013175
0.8     0.02601
0.7     0.03893
0.6     0.051255
0.5     0.06171
0.4     0.068425
0.3     0.06987
0.25    0.068085
0.2     0.064175
0.15    0.05797
0.1     0.048535
0.075   0.04199
0.05    0.034255
0.025   0.023885
0.0125  0.016745
0.01    0.01496
0.006   0.011645
0.004   0.009605
0.002   0.006375
0       0
0.0025  -0.008075
0.005   -0.010455
0.0075  -0.01258
0.01    -0.01377
0.0125  -0.01496
0.025   -0.0187
0.05    -0.023205
0.075   -0.025755
0.1     -0.02754
0.15    -0.029495
0.2     -0.03077
0.25    -0.031535
0.3     -0.032215
0.4     -0.03315
0.5     -0.03349
0.6     -0.03247
0.7     -0.02958
0.8     -0.024055
0.9     -0.015045
0.95    -0.00918
1       0
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Polars for M6 (85%) (m685-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m685-il50,000933.2 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m685-il50,000534.2 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m685-il100,000950.6 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m685-il100,000549.5 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m685-il200,000966.9 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m685-il200,000562.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   m685-il500,000984.8 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m685-il500,000570.7 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m685-il1,000,000985.4 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m685-il1,000,000575.1 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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