MH 121 8.76% (mh121-il)
MH 121 8.76% - Martin Hepperle MH 121 for tip section of a propeller
| Details | Dat file | Parser | |
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(mh121-il) MH 121 8.76% Martin Hepperle MH 121 for tip section of a propeller Max thickness 8.8% at 37.9% chord. Max camber 3% at 62.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 121 8.76% 1.00000000 0.00000000 0.99673797 0.00085150 0.98753891 0.00352659 0.97341690 0.00772780 0.95474371 0.01263896 0.93134847 0.01790405 0.90336313 0.02365142 0.87128597 0.02989427 0.83565023 0.03648448 0.79703464 0.04321792 0.75603131 0.04973358 0.71304543 0.05555745 0.66827638 0.06036372 0.62194317 0.06401863 0.57428530 0.06650354 0.52567223 0.06795023 0.47661830 0.06843706 0.42763480 0.06800259 0.37923177 0.06668134 0.33191002 0.06451917 0.28616015 0.06156216 0.24245302 0.05787462 0.20124046 0.05352195 0.16294421 0.04858951 0.12795980 0.04316386 0.09664381 0.03735173 0.06932353 0.03126124 0.04628547 0.02501144 0.02775970 0.01870368 0.01389310 0.01249514 0.00479068 0.00656288 0.00242620 0.00426765 0.00117353 0.00270737 0.00034693 0.00128230 0.00005495 0.00042685 0.00003105 -0.00030958 0.00034436 -0.00099334 0.00096901 -0.00170880 0.00235716 -0.00281100 0.00423630 -0.00393734 0.00933332 -0.00621728 0.02209641 -0.00995442 0.03998520 -0.01325767 0.06291471 -0.01615295 0.09059174 -0.01867245 0.12265356 -0.02079508 0.15869966 -0.02247370 0.19829137 -0.02364451 0.24095146 -0.02422833 0.28616832 -0.02405832 0.33359195 -0.02289076 0.38302143 -0.02067641 0.43418030 -0.01753351 0.48677017 -0.01369298 0.54032759 -0.00956165 0.59417530 -0.00548781 0.64758980 -0.00173194 0.69981606 0.00149413 0.75008228 0.00402963 0.79761536 0.00577419 0.84165879 0.00668489 0.88148980 0.00678588 0.91643751 0.00616323 0.94589961 0.00496405 0.96933923 0.00339929 0.98632029 0.00178108 0.99657544 0.00050254 1.00000000 0.00000000 |
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Polars for MH 121 8.76% (mh121-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh121-il | 50,000 | 9 | 31.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 50,000 | 5 | 35.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 100,000 | 9 | 53.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 100,000 | 5 | 57.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 200,000 | 9 | 84 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 200,000 | 5 | 82.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 500,000 | 9 | 125.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 500,000 | 5 | 107.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 1,000,000 | 9 | 139.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 1,000,000 | 5 | 117.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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