MH 80 12.72% (mh80-il)
MH 80 12.72% - Martin Hepperle MH 80 for flying wings (hang glider)
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(mh80-il) MH 80 12.72% Martin Hepperle MH 80 for flying wings (hang glider) Max thickness 12.7% at 21.7% chord. Max camber 2.8% at 21.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 80 12.72% 1.00000000 0.00000000 0.99660556 0.00000514 0.98645333 0.00016607 0.96968276 0.00076337 0.94658098 0.00205454 0.91756694 0.00424726 0.88317350 0.00749048 0.84402414 0.01185586 0.80081067 0.01734315 0.75426720 0.02386933 0.70514958 0.03128653 0.65421180 0.03937743 0.60219064 0.04788137 0.54978763 0.05649349 0.49765983 0.06489440 0.44640900 0.07275031 0.39657775 0.07974248 0.34864660 0.08556501 0.30303389 0.08995208 0.26010133 0.09266608 0.22015603 0.09352479 0.18347245 0.09232061 0.15008882 0.08885420 0.11991466 0.08321496 0.09296953 0.07563989 0.06925895 0.06640879 0.04882234 0.05594764 0.03181396 0.04467971 0.01834927 0.03299435 0.00850385 0.02133690 0.00232828 0.01028433 0.00024095 0.00305228 0.00000348 0.00034871 0.00013904 -0.00211528 0.00044985 -0.00359353 0.00098996 -0.00488008 0.00186551 -0.00603085 0.00309213 -0.00715275 0.00545368 -0.00880826 0.00838081 -0.01044426 0.01151718 -0.01192930 0.02649037 -0.01705899 0.04672421 -0.02169346 0.07183447 -0.02565888 0.10162766 -0.02874405 0.13599855 -0.03096346 0.17464593 -0.03250071 0.21708451 -0.03347591 0.26280322 -0.03394179 0.31125714 -0.03395360 0.36187560 -0.03354703 0.41406444 -0.03276581 0.46721388 -0.03163888 0.52070354 -0.03020434 0.57390980 -0.02848532 0.62621187 -0.02651289 0.67699845 -0.02429873 0.72567384 -0.02185281 0.77168250 -0.01912550 0.81461756 -0.01606837 0.85417627 -0.01277466 0.89000484 -0.00947188 0.92167906 -0.00641121 0.94871229 -0.00383528 0.97057090 -0.00191386 0.98671189 -0.00071077 0.99664289 -0.00014303 1.00000000 0.00000000 |
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Polars for MH 80 12.72% (mh80-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh80-il | 50,000 | 9 | 12.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 50,000 | 5 | 22.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh80-il | 100,000 | 9 | 28.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 100,000 | 5 | 39.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh80-il | 200,000 | 9 | 50.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 200,000 | 5 | 58.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh80-il | 500,000 | 9 | 82.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 500,000 | 5 | 85.7 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh80-il | 1,000,000 | 9 | 109.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 1,000,000 | 5 | 108.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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