MH 201 13.08% (mh201-il)
MH 201 13.08% - Martin Hepperle MH 201 for a canard airplane (canard)
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(mh201-il) MH 201 13.08% Martin Hepperle MH 201 for a canard airplane (canard) Max thickness 13% at 38.1% chord. Max camber 2.5% at 48.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 201 13.08% 1.00000000 0.00000000 0.99656789 0.00095473 0.98687599 0.00389591 0.97196794 0.00851415 0.95226366 0.01402658 0.92767454 0.02006559 0.89837640 0.02670727 0.86485652 0.03392207 0.82762512 0.04156867 0.78722794 0.04947216 0.74423437 0.05741170 0.69923009 0.06512321 0.65280025 0.07223609 0.60530062 0.07828560 0.55687451 0.08310525 0.50788998 0.08677991 0.45887051 0.08929239 0.41027604 0.09059454 0.36257864 0.09069796 0.31626235 0.08960164 0.27178729 0.08731824 0.22959145 0.08386618 0.19007998 0.07928766 0.15363166 0.07363032 0.12056975 0.06695830 0.09116986 0.05936158 0.06565468 0.05096868 0.04422060 0.04193182 0.02698038 0.03241454 0.01397005 0.02266973 0.00518508 0.01307097 0.00085149 0.00482642 0.00023039 0.00236360 0.00000043 0.00009610 0.00008139 -0.00127830 0.00040774 -0.00248990 0.00107413 -0.00360381 0.00208167 -0.00472355 0.00409681 -0.00642000 0.00665868 -0.00813782 0.01995142 -0.01428476 0.03767845 -0.01977123 0.06027978 -0.02478188 0.08754050 -0.02917637 0.11919577 -0.03288123 0.15494345 -0.03584764 0.19443073 -0.03806197 0.23726330 -0.03953853 0.28295446 -0.04033285 0.33093935 -0.04043141 0.38068971 -0.03978034 0.43171287 -0.03837672 0.48343059 -0.03628783 0.53518729 -0.03344972 0.58648383 -0.02970569 0.63695210 -0.02494143 0.68647091 -0.01908444 0.73516675 -0.01258226 0.78262750 -0.00641108 0.82788647 -0.00126676 0.86992377 0.00246584 0.90771526 0.00459957 0.94026672 0.00506834 0.96644799 0.00401635 0.98523920 0.00217691 0.99634706 0.00059777 1.00000000 0.00000000 |
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Polars for MH 201 13.08% (mh201-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh201-il | 50,000 | 9 | 33.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh201-il | 50,000 | 5 | 34.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh201-il | 100,000 | 9 | 55 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh201-il | 100,000 | 5 | 52.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh201-il | 200,000 | 9 | 73.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh201-il | 200,000 | 5 | 67 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh201-il | 500,000 | 9 | 95.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh201-il | 500,000 | 5 | 85.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh201-il | 1,000,000 | 9 | 113.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh201-il | 1,000,000 | 5 | 95.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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