MH 113 14.62% (mh113-il)
MH 113 14.62% - Martin Hepperle MH 113 for a propeller for ultralight
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(mh113-il) MH 113 14.62% Martin Hepperle MH 113 for a propeller for ultralight Max thickness 14.7% at 29.7% chord. Max camber 6.4% at 47.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 113 14.62% 1.00000000 0.00000000 0.99657911 0.00129859 0.98693705 0.00520599 0.97212357 0.01135726 0.95257144 0.01898648 0.92829218 0.02772077 0.89956132 0.03753655 0.86691136 0.04827937 0.83087727 0.05966726 0.79197587 0.07136829 0.75069934 0.08303447 0.70752493 0.09431152 0.66290785 0.10483599 0.61722787 0.11424445 0.57079623 0.12228128 0.52396079 0.12878840 0.47709646 0.13364568 0.43058995 0.13677292 0.38483958 0.13811951 0.34024152 0.13766085 0.29718995 0.13539236 0.25604833 0.13132100 0.21714499 0.12549098 0.18077094 0.11797452 0.14716671 0.10890207 0.11656500 0.09846885 0.08919680 0.08689463 0.06526129 0.07441188 0.04491583 0.06128609 0.02828712 0.04781828 0.01547607 0.03434589 0.00654829 0.02121442 0.00144037 0.00885691 0.00009164 -0.00197262 0.00326044 -0.00986391 0.01232056 -0.01515340 0.02750123 -0.01912951 0.04823829 -0.02180405 0.07429146 -0.02316140 0.10544287 -0.02324596 0.14142733 -0.02214665 0.18192638 -0.01998599 0.22655720 -0.01692333 0.27486968 -0.01313926 0.32634580 -0.00883033 0.38042147 -0.00418990 0.43649054 0.00056375 0.49390135 0.00520970 0.55196243 0.00949915 0.60991651 0.01318332 0.66695052 0.01602203 0.72218249 0.01781699 0.77468331 0.01845890 0.82354878 0.01794965 0.86791482 0.01636346 0.90699372 0.01386781 0.94006831 0.01063360 0.96634857 0.00693486 0.98515215 0.00341917 0.99631237 0.00090458 1.00000000 0.00000000 |
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Polars for MH 113 14.62% (mh113-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh113-il | 50,000 | 9 | 6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh113-il | 50,000 | 5 | 20.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh113-il | 100,000 | 9 | 50.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh113-il | 100,000 | 5 | 56 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh113-il | 200,000 | 9 | 84.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh113-il | 200,000 | 5 | 83.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh113-il | 500,000 | 9 | 124.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh113-il | 500,000 | 5 | 114.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh113-il | 1,000,000 | 9 | 153 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh113-il | 1,000,000 | 5 | 132.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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