MILEY M06-13-128 (miley-il)
MILEY M06-13-128 - Miley MO6-13-128 airfoil
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(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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Polars for MILEY M06-13-128 (miley-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| miley-il | 50,000 | 9 | 5.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 50,000 | 5 | 11 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 100,000 | 9 | 23.5 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 100,000 | 5 | 23.2 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 200,000 | 9 | 61.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 200,000 | 5 | 62.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 500,000 | 9 | 122.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 500,000 | 5 | 121.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 1,000,000 | 9 | 168 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 1,000,000 | 5 | 157.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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