MH 62 9.3% (mh62-il)
MH 62 9.3% - Martin Hepperle MH 62 for flying wings
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(mh62-il) MH 62 9.3% Martin Hepperle MH 62 for flying wings Max thickness 9.3% at 26.9% chord. Max camber 1.6% at 36.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 62 9.3% 1.00000000 0.00000000 0.99672320 -0.00005436 0.98685283 -0.00004227 0.97053131 0.00044022 0.94815429 0.00166033 0.92015682 0.00376111 0.88708273 0.00688970 0.84963205 0.01106850 0.80850880 0.01615624 0.76438713 0.02195639 0.71793385 0.02821659 0.66979461 0.03462645 0.62051197 0.04081389 0.57051869 0.04648866 0.52022803 0.05143382 0.47002954 0.05552368 0.42036402 0.05871060 0.37172105 0.06095135 0.32458149 0.06218839 0.27941266 0.06237129 0.23663376 0.06143558 0.19660300 0.05936305 0.15965048 0.05616726 0.12606278 0.05190115 0.09610193 0.04664817 0.06999052 0.04051440 0.04789620 0.03361471 0.02988773 0.02613699 0.01603412 0.01837117 0.00637213 0.01069211 0.00178293 0.00505036 0.00077015 0.00307015 0.00016380 0.00124513 0.00000237 0.00014025 0.00009452 -0.00083055 0.00051805 -0.00173743 0.00125746 -0.00267469 0.00282697 -0.00412213 0.00489391 -0.00561505 0.00662611 -0.00668823 0.01795493 -0.01168918 0.03425341 -0.01646465 0.05527811 -0.02080445 0.08082177 -0.02452171 0.11068708 -0.02745559 0.14470193 -0.02952059 0.18262595 -0.03071456 0.22417611 -0.03108025 0.26897575 -0.03072687 0.31657049 -0.02974802 0.36646434 -0.02824858 0.41812828 -0.02633552 0.47098183 -0.02414541 0.52440200 -0.02178507 0.57774515 -0.01936355 0.63035485 -0.01695180 0.68158415 -0.01461807 0.73080181 -0.01239832 0.77740590 -0.01033227 0.82082839 -0.00843907 0.86053021 -0.00675058 0.89600848 -0.00526331 0.92681587 -0.00397449 0.95256426 -0.00285512 0.97292940 -0.00187770 0.98770717 -0.00097268 0.99684228 -0.00026167 1.00000000 0.00000000 |
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Polars for MH 62 9.3% (mh62-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh62-il | 50,000 | 9 | 28.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 50,000 | 5 | 33.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 100,000 | 9 | 45 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 100,000 | 5 | 46 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 200,000 | 9 | 60.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 200,000 | 5 | 58.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 500,000 | 9 | 80.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 500,000 | 5 | 75 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh62-il | 1,000,000 | 9 | 94.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh62-il | 1,000,000 | 5 | 87.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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