MH 112 Airfoil (mh112-il)
MH 112 Airfoil - Martin Hepperle MH 112 for a propeller for ultralight (root)
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(mh112-il) MH 112 Airfoil Martin Hepperle MH 112 for a propeller for ultralight (root) Max thickness 16.2% at 31.8% chord. Max camber 6.7% at 48.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 112 Airfoil 1.00000000 0.00000000 0.99649058 0.00136330 0.98660368 0.00547709 0.97143035 0.01199665 0.95144341 0.02016652 0.92670131 0.02961565 0.89752683 0.04030415 0.86449272 0.05205068 0.82816738 0.06453411 0.78908692 0.07737681 0.74774914 0.09018520 0.70462892 0.10256493 0.66017070 0.11411477 0.61473811 0.12444329 0.56862372 0.13327372 0.52216328 0.14043722 0.47572481 0.14579553 0.42968835 0.14925105 0.38444902 0.15070762 0.34032550 0.15006923 0.29755052 0.14737924 0.25646503 0.14284242 0.21755026 0.13658085 0.18117792 0.12859862 0.14758049 0.11898092 0.11697865 0.10791633 0.08960025 0.09562226 0.06563801 0.08233394 0.04525115 0.06832104 0.02856435 0.05388872 0.01569521 0.03937555 0.00671543 0.02509061 0.00153301 0.01141669 0.00001242 -0.00096463 0.00024127 -0.00410677 0.00081387 -0.00722284 0.00173454 -0.01004675 0.00255195 -0.01173186 0.00357223 -0.01319148 0.00490827 -0.01446260 0.00659548 -0.01564798 0.00965829 -0.01731512 0.01330108 -0.01886542 0.02415012 -0.02214263 0.04402578 -0.02550975 0.06928121 -0.02743757 0.09968072 -0.02797448 0.13497116 -0.02718773 0.17484399 -0.02520125 0.21893213 -0.02216602 0.26679856 -0.01826931 0.31793754 -0.01370545 0.37179503 -0.00867603 0.42777046 -0.00338197 0.48527553 0.00198303 0.54373728 0.00709861 0.60239110 0.01153371 0.66029295 0.01496970 0.71646983 0.01721591 0.76993975 0.01818017 0.81975105 0.01787304 0.86499658 0.01639631 0.90486064 0.01394373 0.93860949 0.01072049 0.96545654 0.00702160 0.98472163 0.00348974 0.99619815 0.00093082 1.00000000 0.00000000 |
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Polars for MH 112 Airfoil (mh112-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh112-il | 50,000 | 9 | 5.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 50,000 | 5 | 14.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 100,000 | 9 | 37.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 100,000 | 5 | 48.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 200,000 | 9 | 80 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 200,000 | 5 | 79.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 500,000 | 9 | 120 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 500,000 | 5 | 109.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 1,000,000 | 9 | 147.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 1,000,000 | 5 | 126.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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