MH 115 11.06% (mh115-il)
MH 115 11.06% - Martin Hepperle MH 115 for a propeller for ultralight
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(mh115-il) MH 115 11.06% Martin Hepperle MH 115 for a propeller for ultralight Max thickness 11.1% at 29.8% chord. Max camber 5.5% at 46% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 115 11.06% 1.00000000 0.00000000 0.99674566 0.00104546 0.98749507 0.00420491 0.97313696 0.00917838 0.95406083 0.01529495 0.93027275 0.02221117 0.90199575 0.02990813 0.86969551 0.03827613 0.83385141 0.04708744 0.79491906 0.05607895 0.75332317 0.06501166 0.70953970 0.07369232 0.66408448 0.08188293 0.61744199 0.08932477 0.57006351 0.09577091 0.52236480 0.10100258 0.47472315 0.10485199 0.42750717 0.10721862 0.38107486 0.10805718 0.33581107 0.10739733 0.29213489 0.10526383 0.25043484 0.10168814 0.21107556 0.09672020 0.17438403 0.09043777 0.14065894 0.08294253 0.11015046 0.07436606 0.08306868 0.06488165 0.05959692 0.05472346 0.03994100 0.04413071 0.02421451 0.03330030 0.01239244 0.02252916 0.00442595 0.01233725 0.00069857 0.00437441 0.00016371 0.00197385 0.00000179 -0.00019390 0.00011571 -0.00148174 0.00045986 -0.00258950 0.00112633 -0.00357520 0.00211854 -0.00453745 0.00408531 -0.00594230 0.00657061 -0.00729619 0.00768550 -0.00781423 0.02015328 -0.01156879 0.03800525 -0.01423278 0.06110941 -0.01574891 0.08933311 -0.01613566 0.12247340 -0.01547900 0.16025579 -0.01389519 0.20233415 -0.01153157 0.24829570 -0.00855767 0.29764598 -0.00517063 0.34981349 -0.00155002 0.40418640 0.00213342 0.46011715 0.00571533 0.51692182 0.00902612 0.57388416 0.01191204 0.63026148 0.01422380 0.68528991 0.01584103 0.73819142 0.01666217 0.78818207 0.01663427 0.83448365 0.01574448 0.87633804 0.01405771 0.91305213 0.01170364 0.94399942 0.00884122 0.96852822 0.00569981 0.98609072 0.00278939 0.99654075 0.00073435 1.00000000 0.00000000 |
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Polars for MH 115 11.06% (mh115-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh115-il | 50,000 | 9 | 28.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh115-il | 50,000 | 5 | 37.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh115-il | 100,000 | 9 | 61.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh115-il | 100,000 | 5 | 64.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh115-il | 200,000 | 9 | 91.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh115-il | 200,000 | 5 | 90 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh115-il | 500,000 | 9 | 130.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh115-il | 500,000 | 5 | 120.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh115-il | 1,000,000 | 9 | 158.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh115-il | 1,000,000 | 5 | 140.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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