MH 70 11.08% (mh70-il)
MH 70 11.08% - Martin Hepperle MH 70 for fying wing (full size)
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(mh70-il) MH 70 11.08% Martin Hepperle MH 70 for fying wing (full size) Max thickness 11.1% at 29.4% chord. Max camber 3% at 39.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 70 11.08% 1.00000000 0.00000000 0.99663874 0.00038973 0.98681861 0.00160039 0.97091284 0.00366465 0.94918585 0.00661587 0.92201087 0.01055332 0.88990605 0.01555023 0.85351341 0.02156423 0.81348356 0.02843088 0.77045027 0.03593166 0.72505209 0.04381288 0.67791513 0.05175439 0.62958956 0.05939579 0.58054074 0.06640360 0.53117433 0.07249554 0.48183152 0.07749388 0.43291812 0.08134625 0.38490056 0.08398008 0.33821526 0.08532374 0.29327034 0.08533399 0.25046211 0.08401195 0.21017875 0.08136709 0.17277302 0.07742995 0.13857039 0.07223969 0.10783154 0.06584860 0.08075868 0.05834736 0.05748979 0.04986763 0.03810212 0.04060855 0.02264005 0.03085990 0.01116110 0.02097603 0.00368716 0.01137304 0.00049015 0.00381228 0.00007503 0.00139590 0.00002872 -0.00081542 0.00021629 -0.00214578 0.00062912 -0.00330577 0.00136089 -0.00434878 0.00241995 -0.00537081 0.00449418 -0.00687682 0.00709496 -0.00835404 0.00853955 -0.00906297 0.02171085 -0.01371562 0.04014361 -0.01784573 0.06353610 -0.02131274 0.09165680 -0.02399974 0.12427053 -0.02584970 0.16111728 -0.02684532 0.20189931 -0.02703766 0.24623689 -0.02652725 0.29366811 -0.02542450 0.34368819 -0.02383141 0.39575196 -0.02187620 0.44925704 -0.01969020 0.50355203 -0.01739603 0.55796000 -0.01508522 0.61178825 -0.01282331 0.66437716 -0.01063056 0.71510432 -0.00854905 0.76335935 -0.00661876 0.80855024 -0.00488174 0.85011975 -0.00336117 0.88754749 -0.00209099 0.92034639 -0.00109300 0.94806277 -0.00039212 0.97027225 0.00001004 0.98657712 0.00013332 0.99660243 0.00006156 1.00000000 0.00000000 |
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Polars for MH 70 11.08% (mh70-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh70-il | 50,000 | 9 | 27.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 50,000 | 5 | 35.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 100,000 | 9 | 50.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 100,000 | 5 | 52.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 200,000 | 9 | 70.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 200,000 | 5 | 67.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 500,000 | 9 | 95 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 500,000 | 5 | 87.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 1,000,000 | 9 | 112.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 1,000,000 | 5 | 103.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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