MH 117 9.8% (mh117-il)
MH 117 9.8% - Martin Hepperle MH 117 for a propeller for ultralight (tip)
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(mh117-il) MH 117 9.8% Martin Hepperle MH 117 for a propeller for ultralight (tip) Max thickness 9.8% at 29.1% chord. Max camber 2.7% at 44.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 117 9.8% 1.00000000 0.00000000 0.99669031 0.00049003 0.98707731 0.00207033 0.97177624 0.00475426 0.95120013 0.00825965 0.92554805 0.01241627 0.89513234 0.01723294 0.86042844 0.02267080 0.82194932 0.02862516 0.78024605 0.03496400 0.73589923 0.04150880 0.68948289 0.04804150 0.64155561 0.05432933 0.59265387 0.06013032 0.54328520 0.06520439 0.49390561 0.06931828 0.44491485 0.07229087 0.39667271 0.07399667 0.34949257 0.07441820 0.30376269 0.07365704 0.25995386 0.07178323 0.21850111 0.06883168 0.17980252 0.06485100 0.14421934 0.05990381 0.11207729 0.05406639 0.08364666 0.04742811 0.05914156 0.04011465 0.03873701 0.03230144 0.02260069 0.02418269 0.01080931 0.01593784 0.00329342 0.00791465 0.00180844 0.00553261 0.00078264 0.00337629 0.00016559 0.00137780 0.00000240 0.00015663 0.00009545 -0.00093355 0.00051520 -0.00196476 0.00124174 -0.00303020 0.00277989 -0.00467095 0.00480487 -0.00634666 0.01110910 -0.01022340 0.02423919 -0.01556325 0.04202841 -0.02006888 0.06458390 -0.02353976 0.09186189 -0.02598343 0.12369190 -0.02742948 0.15984299 -0.02793392 0.20001108 -0.02758763 0.24382591 -0.02650300 0.29085133 -0.02481832 0.34057636 -0.02268597 0.39242047 -0.02024403 0.44577230 -0.01760693 0.49999633 -0.01488444 0.55444002 -0.01217351 0.60844101 -0.00956485 0.66133467 -0.00713548 0.71246137 -0.00495190 0.76117830 -0.00306340 0.80686551 -0.00151205 0.84892722 -0.00032506 0.88679810 0.00048717 0.91995456 0.00093779 0.94791780 0.00105862 0.97026156 0.00091038 0.98661057 0.00057426 0.99662097 0.00018251 1.00000000 0.00000000 |
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Polars for MH 117 9.8% (mh117-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh117-il | 50,000 | 9 | 36.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 50,000 | 5 | 38.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 100,000 | 9 | 56.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 100,000 | 5 | 55.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 200,000 | 9 | 77 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 200,000 | 5 | 72 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 500,000 | 9 | 102.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 500,000 | 5 | 90.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 1,000,000 | 9 | 120.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 1,000,000 | 5 | 100.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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