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MILEY M06-13-128 (miley-il)

MILEY M06-13-128 - Miley MO6-13-128 airfoil


Airfoil miley-il
Details Dat file Parser  
(miley-il) MILEY M06-13-128
Miley MO6-13-128 airfoil
Max thickness 12.9% at 35% chord.
Max camber 4.9% at 35% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
MILEY M06-13-128
1.00000  0.00000
0.99896  0.00015
0.99152  0.00088
0.97756  0.00198
0.95718  0.00370
0.93068  0.00631
0.89849  0.01002
0.86112  0.01499
0.81923  0.02139 
0.77354  0.02930
0.72493  0.03878
0.67434  0.04980
0.62288  0.06225
0.57180  0.07584
0.52265  0.09002
0.47756  0.10309
0.43510  0.11094
0.39263  0.11489
0.35032  0.11617
0.30873  0.11531
0.26838  0.11256
0.22975  0.10814
0.19328  0.10220
0.15942  0.09487
0.12857  0.08605
0.10057  0.07583
0.07558  0.06460
0.05382  0.05305
0.03551  0.04122
0.02083  0.02960
0.00994  0.01862
0.00296  0.00878
0.00098  0.00452
0.00005  0.00087
0.00030  -.00183
0.00233  -.00372
0.01203  -.00669
0.02803  -.00901   
0.04987  -.01077
0.07718  -.01203
0.10959  -.01287
0.14667  -.01333
0.18796  -.01349
0.23296  -.01339
0.28111  -.01308
0.33185  -.01260
0.38456  -.01200
0.43862  -.01129
0.49338  -.01053
0.54820  -.00972
0.60242  -.00890
0.65541  -.00809
0.70652  -.00729
0.75516  -.00652
0.80073  -.00577
0.84269  -.00506
0.88053  -.00437
0.91379  -.00370
0.94205  -.00302
0.96496  -.00228
0.98232  -.00147
0.99393  -.00073
0.99942  -.00014
1.00000  0.00000
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Lednicer format dat file
Selig format dat file

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Polars for MILEY M06-13-128 (miley-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   miley-il50,00095.8 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   miley-il50,000511 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   miley-il100,000923.5 at α=13°Mach=0 Ncrit=9Xfoil predictionDetails
   miley-il100,000523.2 at α=12.25°Mach=0 Ncrit=5Xfoil predictionDetails
   miley-il200,000961.2 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   miley-il200,000562.8 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   miley-il500,0009122.8 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   miley-il500,0005121.4 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   miley-il1,000,0009168 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   miley-il1,000,0005157.6 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
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