MH 116 9.84% (mh116-il)
MH 116 9.84% - Martin Hepperle MH 116 for a propeller for ultralight
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(mh116-il) MH 116 9.84% Martin Hepperle MH 116 for a propeller for ultralight Max thickness 9.9% at 32.4% chord. Max camber 4.1% at 46.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 116 9.84% 1.00000000 0.00000000 0.99670146 0.00074814 0.98721743 0.00307583 0.97230854 0.00688054 0.95240976 0.01171791 0.92766355 0.01732983 0.89836484 0.02369937 0.86500106 0.03073152 0.82808656 0.03824262 0.78813381 0.04599730 0.74564655 0.05374885 0.70111701 0.06123259 0.65502194 0.06819657 0.60781241 0.07438806 0.55991093 0.07960072 0.51172865 0.08365638 0.46365997 0.08642268 0.41606636 0.08779284 0.36926585 0.08776891 0.32364632 0.08644796 0.27966531 0.08391535 0.23775427 0.08021674 0.19830559 0.07542539 0.16168504 0.06962024 0.12821458 0.06291334 0.09819465 0.05543568 0.07189000 0.04733540 0.04951823 0.03875778 0.03121401 0.02989438 0.01707861 0.02098180 0.00710579 0.01236090 0.00164447 0.00513736 0.00068511 0.00304275 0.00012824 0.00114121 0.00000000 0.00000460 0.00012587 -0.00098049 0.00058603 -0.00188406 0.00136572 -0.00280442 0.00299737 -0.00420676 0.00512857 -0.00563013 0.01652794 -0.01043038 0.03235571 -0.01419815 0.05316147 -0.01700865 0.07888662 -0.01880306 0.10939639 -0.01958813 0.14449266 -0.01943482 0.18388770 -0.01845562 0.22722412 -0.01678535 0.27406730 -0.01459252 0.32390001 -0.01205138 0.37612573 -0.00932796 0.43011154 -0.00654727 0.48519647 -0.00383863 0.54069749 -0.00129973 0.59591933 0.00096771 0.65016027 0.00289580 0.70272230 0.00441674 0.75292169 0.00550059 0.80009726 0.00611414 0.84361040 0.00625919 0.88285307 0.00594510 0.91725959 0.00522485 0.94630943 0.00415177 0.96949175 0.00283087 0.98634699 0.00147768 0.99657154 0.00041241 1.00000000 0.00000000 |
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Polars for MH 116 9.84% (mh116-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh116-il | 50,000 | 9 | 39 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh116-il | 50,000 | 5 | 39.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh116-il | 100,000 | 9 | 63 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh116-il | 100,000 | 5 | 63 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh116-il | 200,000 | 9 | 89.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh116-il | 200,000 | 5 | 86.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh116-il | 500,000 | 9 | 125.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh116-il | 500,000 | 5 | 113.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh116-il | 1,000,000 | 9 | 150.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh116-il | 1,000,000 | 5 | 131 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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