MH 110 10.01% (mh110-il)
MH 110 10.01% - Martin Hepperle MH 110 for stall controlled wind turbines (tip)
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(mh110-il) MH 110 10.01% Martin Hepperle MH 110 for stall controlled wind turbines (tip) Max thickness 10% at 23.9% chord. Max camber 1% at 15.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 110 10.01% 1.00000000 0.00000000 0.99653679 -0.00000839 0.98640394 0.00020868 0.97015295 0.00088858 0.94817712 0.00187970 0.92061713 0.00312964 0.88774439 0.00482284 0.85005668 0.00710281 0.80812280 0.01002942 0.76257153 0.01361933 0.71407609 0.01783903 0.66333945 0.02260907 0.61107819 0.02780629 0.55800744 0.03326766 0.50482605 0.03879780 0.45220316 0.04417530 0.40076651 0.04916328 0.35109229 0.05351815 0.30369808 0.05700000 0.25903745 0.05938370 0.21749907 0.06046023 0.17940788 0.06005282 0.14504302 0.05792865 0.11434721 0.05380340 0.08696462 0.04785904 0.06286228 0.04069252 0.04230701 0.03279183 0.02555418 0.02451705 0.01281496 0.01623683 0.00429649 0.00837148 0.00211665 0.00545033 0.00096208 0.00340260 0.00023711 0.00150577 0.00001434 0.00034898 0.00006123 -0.00067806 0.00045103 -0.00165194 0.00116088 -0.00266955 0.00269267 -0.00425311 0.00473182 -0.00589158 0.01020191 -0.00928503 0.02329198 -0.01496193 0.04120440 -0.02035040 0.06381301 -0.02526009 0.09094732 -0.02958794 0.12236865 -0.03326391 0.15780899 -0.03623346 0.19695727 -0.03849081 0.23943286 -0.04006268 0.28478797 -0.04097415 0.33254591 -0.04124334 0.38220182 -0.04089743 0.43324080 -0.03996525 0.48514078 -0.03851948 0.53730757 -0.03665724 0.58911977 -0.03440665 0.64003009 -0.03178595 0.68950142 -0.02887417 0.73697819 -0.02575203 0.78192326 -0.02249320 0.82382388 -0.01917110 0.86219604 -0.01586085 0.89658864 -0.01263340 0.92658689 -0.00956236 0.95181035 -0.00668459 0.97203228 -0.00402294 0.98711684 -0.00181207 0.99667613 -0.00043813 1.00000000 0.00000000 |
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Polars for MH 110 10.01% (mh110-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh110-il | 50,000 | 9 | 16.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 50,000 | 5 | 25.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 100,000 | 9 | 39 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 100,000 | 5 | 41 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 200,000 | 9 | 56.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 200,000 | 5 | 56 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 500,000 | 9 | 78.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 500,000 | 5 | 75.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 1,000,000 | 9 | 94.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 1,000,000 | 5 | 88.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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