MH 23 8% (mh23-il)
MH 23 8% - Martin Hepperle MH 23 for F3D Pylon Racing (extended laminar flow)
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(mh23-il) MH 23 8% Martin Hepperle MH 23 for F3D Pylon Racing (extended laminar flow) Max thickness 8% at 37.5% chord. Max camber 1.2% at 42.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 23 8% 1.00000000 0.00000000 0.99654891 0.00021002 0.98638164 0.00106437 0.96998124 0.00296595 0.94800139 0.00610570 0.92118921 0.01045067 0.89031194 0.01575297 0.85609439 0.02147937 0.81881667 0.02686673 0.77833061 0.03162776 0.73482769 0.03593914 0.68882550 0.03985290 0.64081070 0.04331623 0.59131663 0.04632354 0.54090044 0.04880706 0.49010217 0.05072471 0.43946837 0.05202613 0.38954323 0.05268363 0.34085802 0.05265035 0.29391873 0.05190854 0.24921148 0.05043165 0.20718720 0.04821694 0.16825913 0.04525334 0.13278111 0.04156398 0.10107217 0.03718625 0.07339004 0.03218696 0.04995254 0.02665608 0.03090007 0.02072236 0.01634588 0.01457859 0.00633460 0.00848345 0.00187296 0.00419942 0.00083390 0.00259110 0.00019669 0.00110607 0.00000845 0.00021283 0.00006741 -0.00055535 0.00045537 -0.00125931 0.00116150 -0.00198573 0.00268384 -0.00310871 0.00470453 -0.00428571 0.00674568 -0.00531418 0.01818877 -0.00930151 0.03475010 -0.01303636 0.05627852 -0.01634982 0.08264936 -0.01916279 0.11366235 -0.02149126 0.14901824 -0.02339855 0.18829159 -0.02493191 0.23103070 -0.02608303 0.27674146 -0.02685342 0.32493807 -0.02720281 0.37513360 -0.02716554 0.42678480 -0.02678840 0.47929590 -0.02613063 0.53206388 -0.02520550 0.58448190 -0.02405271 0.63594771 -0.02267570 0.68586872 -0.02110271 0.73368042 -0.01931914 0.77884998 -0.01735713 0.82085481 -0.01517772 0.85934130 -0.01277321 0.89392583 -0.01030911 0.92410094 -0.00780159 0.94970175 -0.00516897 0.97065426 -0.00275126 0.98651517 -0.00101933 0.99654701 -0.00019154 1.00000000 0.00000000 |
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Polars for MH 23 8% (mh23-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh23-il | 50,000 | 9 | 34.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh23-il | 50,000 | 5 | 33.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh23-il | 100,000 | 9 | 50 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh23-il | 100,000 | 5 | 45.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh23-il | 200,000 | 9 | 66.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh23-il | 200,000 | 5 | 57.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh23-il | 500,000 | 9 | 83.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh23-il | 500,000 | 5 | 66.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh23-il | 1,000,000 | 9 | 83.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh23-il | 1,000,000 | 5 | 72.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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