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M6 (65%) (m665-il)

M6 (65%) - NACA/Munk M6 (65%)


Airfoil m665-il
Details Dat file Parser  
(m665-il) M6 (65%)
NACA/Munk M6 (65%)
Max thickness 7.8% at 30% chord.
Max camber 1.4% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
 
M6 (65%)     
1       0
0.95    0.0052
0.9     0.010075
0.8     0.01989
0.7     0.02977
0.6     0.039195
0.5     0.04719
0.4     0.052325
0.3     0.05343
0.25    0.052065
0.2     0.049075
0.15    0.04433
0.1     0.037115
0.075   0.03211
0.05    0.026195
0.025   0.018265
0.0125  0.012805
0.01    0.01144
0.006   0.008905
0.004   0.007345
0.002   0.004875
0       0
0.0025  -0.006175
0.005   -0.007995
0.0075  -0.00962
0.01    -0.01053
0.0125  -0.01144
0.025   -0.0143
0.05    -0.017745
0.075   -0.019695
0.1     -0.02106
0.15    -0.022555
0.2     -0.02353
0.25    -0.024115
0.3     -0.024635
0.4     -0.02535
0.5     -0.02561
0.6     -0.02483
0.7     -0.02262
0.8     -0.018395
0.9     -0.011505
0.95    -0.00702
1       0
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Polars for M6 (65%) (m665-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   m665-il50,000933.8 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   m665-il50,000533.1 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   m665-il100,000947.3 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   m665-il100,000544.8 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   m665-il200,000960.3 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m665-il200,000555.4 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   m665-il500,000974.7 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   m665-il500,000561.9 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   m665-il1,000,000978.6 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   m665-il1,000,000573.2 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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