MH 78 14.47% (mh78-il)
MH 78 14.47% - Martin Hepperle MH 78 for flying wings (hang glider)
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(mh78-il) MH 78 14.47% Martin Hepperle MH 78 for flying wings (hang glider) Max thickness 14.4% at 22.1% chord. Max camber 1.9% at 17.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 78 14.47% 1.00000000 0.00000000 0.99647376 -0.00005769 0.98594343 -0.00006167 0.96857920 0.00031010 0.94469065 0.00133916 0.91471313 0.00325525 0.87919370 0.00623043 0.83877336 0.01036549 0.79416760 0.01568975 0.74614368 0.02215224 0.69549919 0.02963028 0.64303838 0.03792739 0.58955279 0.04679051 0.53580093 0.05591397 0.48249441 0.06496290 0.43028441 0.07358030 0.37975519 0.08141319 0.33141918 0.08811752 0.28571789 0.09338432 0.24302652 0.09693173 0.20366177 0.09853301 0.16790530 0.09791980 0.13576599 0.09481689 0.10710138 0.08926263 0.08186069 0.08142652 0.05989520 0.07157890 0.04115205 0.06026510 0.02583034 0.04799225 0.01408202 0.03509813 0.00588632 0.02196825 0.00117701 0.00922609 0.00004071 -0.00160454 0.00037773 -0.00474011 0.00106694 -0.00762752 0.00173681 -0.00938226 0.00262341 -0.01093910 0.00383435 -0.01234483 0.00539475 -0.01370379 0.00826371 -0.01569514 0.01170942 -0.01764406 0.02810394 -0.02422507 0.04904288 -0.02987339 0.07490483 -0.03490330 0.10530986 -0.03917904 0.13998895 -0.04253225 0.17874711 -0.04496957 0.22121381 -0.04664469 0.26687101 -0.04764926 0.31517512 -0.04803149 0.36555838 -0.04783093 0.41743222 -0.04708522 0.47019348 -0.04582658 0.52322981 -0.04409010 0.57592623 -0.04190422 0.62767130 -0.03929951 0.67786291 -0.03629286 0.72591398 -0.03289037 0.77128261 -0.02902518 0.81362617 -0.02461843 0.85274328 -0.01980018 0.88835211 -0.01488937 0.92005707 -0.01025828 0.94735107 -0.00627581 0.96962738 -0.00322749 0.98622391 -0.00124894 0.99650893 -0.00026574 1.00000000 0.00000000 |
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Polars for MH 78 14.47% (mh78-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh78-il | 50,000 | 9 | 9.9 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh78-il | 50,000 | 5 | 18.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh78-il | 100,000 | 9 | 22.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh78-il | 100,000 | 5 | 33.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh78-il | 200,000 | 9 | 42.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh78-il | 200,000 | 5 | 51.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh78-il | 500,000 | 9 | 73.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh78-il | 500,000 | 5 | 77.3 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh78-il | 1,000,000 | 9 | 99.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh78-il | 1,000,000 | 5 | 97.2 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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