MH 25 9.98% (mh25-il)
MH 25 9.98% - Martin Hepperle MH 25 for F3D Pylon Racing (extended laminar flow)
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(mh25-il) MH 25 9.98% Martin Hepperle MH 25 for F3D Pylon Racing (extended laminar flow) Max thickness 10% at 42.2% chord. Max camber 1.4% at 42.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 25 9.98% 1.00000000 0.00000000 0.99635051 0.00044823 0.98573137 0.00204140 0.96894107 0.00519871 0.94688038 0.00993961 0.92037370 0.01596838 0.89011954 0.02282430 0.85669024 0.02985118 0.82021659 0.03629489 0.78049149 0.04193268 0.73771056 0.04697095 0.69238447 0.05145822 0.64499206 0.05534558 0.59605623 0.05862203 0.54612430 0.06122491 0.49572697 0.06311117 0.44540326 0.06423869 0.39569004 0.06458276 0.34711360 0.06410878 0.30017618 0.06280648 0.25536234 0.06066464 0.21312332 0.05769242 0.17387529 0.05389664 0.13797800 0.04931573 0.10575823 0.04400481 0.07748459 0.03804852 0.05338824 0.03155294 0.03362650 0.02466585 0.01833367 0.01758842 0.00757463 0.01059496 0.00186535 0.00470621 0.00082048 0.00288211 0.00018458 0.00120135 0.00000512 0.00018681 0.00008206 -0.00069576 0.00049731 -0.00151394 0.00123711 -0.00236167 0.00281860 -0.00367833 0.00491028 -0.00505231 0.01668117 -0.01010252 0.03284835 -0.01455005 0.05403846 -0.01860966 0.08010773 -0.02219502 0.11085035 -0.02530002 0.14595902 -0.02798038 0.18500534 -0.03026407 0.22753533 -0.03213699 0.27305393 -0.03358921 0.32106307 -0.03458492 0.37105343 -0.03513721 0.42247260 -0.03526852 0.47472749 -0.03500919 0.52721868 -0.03435978 0.57934234 -0.03333837 0.63049994 -0.03193727 0.68010142 -0.03016404 0.72758141 -0.02798673 0.77240110 -0.02539979 0.81402717 -0.02225708 0.85232061 -0.01834465 0.88735957 -0.01400994 0.91868469 -0.00982829 0.94576564 -0.00601403 0.96822033 -0.00291374 0.98536058 -0.00093384 0.99624793 -0.00013682 1.00000000 0.00000000 |
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Polars for MH 25 9.98% (mh25-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh25-il | 50,000 | 9 | 34.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 50,000 | 5 | 32.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 100,000 | 9 | 51.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 100,000 | 5 | 48 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 200,000 | 9 | 70.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 200,000 | 5 | 58.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 500,000 | 9 | 78.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 500,000 | 5 | 60.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 1,000,000 | 9 | 75 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 1,000,000 | 5 | 69.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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