MH 114 13.02% (mh114-il)
MH 114 13.02% - Martin Hepperle MH 114 for a propeller for ultralight
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(mh114-il) MH 114 13.02% Martin Hepperle MH 114 for a propeller for ultralight Max thickness 13% at 28.1% chord. Max camber 6.4% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 114 13.02% 1.00000000 0.00000000 0.99667566 0.00127091 0.98731466 0.00508030 0.97294285 0.01102133 0.95394941 0.01828860 0.93028455 0.02649819 0.90217220 0.03564269 0.87010598 0.04559033 0.83458560 0.05609031 0.79610663 0.06685087 0.75515297 0.07756051 0.71219794 0.08789714 0.66769773 0.09753021 0.62204386 0.10612640 0.57556669 0.11344647 0.52862389 0.11933627 0.48159244 0.12368504 0.43486602 0.12642440 0.38885365 0.12751147 0.34396060 0.12692343 0.30058729 0.12465754 0.25910372 0.12072122 0.21984312 0.11515990 0.18310506 0.10804821 0.14914254 0.09951468 0.11819963 0.08974616 0.09051427 0.07895233 0.06629112 0.06735503 0.04568918 0.05520889 0.02883347 0.04280482 0.01580501 0.03047906 0.00665698 0.01863245 0.00139717 0.00777183 0.00021738 0.00285253 0.00000128 0.00020630 0.00015578 -0.00218399 0.00047748 -0.00360344 0.00102029 -0.00482311 0.00188207 -0.00589101 0.00307710 -0.00690420 0.00536346 -0.00833777 0.00818256 -0.00966916 0.01396759 -0.01167125 0.02998040 -0.01489783 0.05146211 -0.01693984 0.07820223 -0.01780217 0.10998679 -0.01752983 0.14654017 -0.01622017 0.18753106 -0.01399145 0.23256226 -0.01100035 0.28117044 -0.00741551 0.33282653 -0.00342225 0.38695746 0.00080409 0.44295096 0.00506331 0.50015235 0.00915869 0.55787098 0.01286723 0.61535885 0.01597279 0.67182118 0.01826471 0.72640660 0.01957527 0.77822736 0.01980849 0.82641818 0.01896858 0.87014991 0.01711775 0.90865700 0.01440675 0.94123377 0.01098584 0.96708092 0.00711905 0.98551223 0.00347938 0.99640825 0.00091297 1.00000000 0.00000000 |
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Polars for MH 114 13.02% (mh114-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh114-il | 50,000 | 9 | 9.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 50,000 | 5 | 26 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 100,000 | 9 | 56.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 100,000 | 5 | 60.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 200,000 | 9 | 89.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 200,000 | 5 | 88.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 500,000 | 9 | 131.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 500,000 | 5 | 121 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 1,000,000 | 9 | 161 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 1,000,000 | 5 | 140.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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