MH 200 12.97% (mh200-il)
MH 200 12.97% - Martin Hepperle MH 200 for a canard airplane (main wing)
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(mh200-il) MH 200 12.97% Martin Hepperle MH 200 for a canard airplane (main wing) Max thickness 13% at 39.5% chord. Max camber 2.1% at 49.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 200 12.97% 1.00000000 0.00000000 0.99649500 0.00069704 0.98645609 0.00294186 0.97076930 0.00667102 0.94991971 0.01138589 0.92401295 0.01684286 0.89335961 0.02311601 0.85853187 0.03017901 0.82013428 0.03788260 0.77880287 0.04601904 0.73518677 0.05430353 0.68993711 0.06238477 0.64368050 0.06973364 0.59665380 0.07568313 0.54874065 0.08004849 0.50018351 0.08307833 0.45151296 0.08486339 0.40319441 0.08541917 0.35571692 0.08481364 0.30959347 0.08308417 0.26530396 0.08025749 0.22329039 0.07637741 0.18398182 0.07151905 0.14780067 0.06574033 0.11509401 0.05907667 0.08612403 0.05160462 0.06110030 0.04344873 0.04017907 0.03478990 0.02349151 0.02588057 0.01117972 0.01702927 0.00336229 0.00856940 0.00149051 0.00536311 0.00057296 0.00310588 0.00008069 0.00101423 0.00000589 -0.00025882 0.00019148 -0.00138414 0.00072371 -0.00243308 0.00159345 -0.00350752 0.00339509 -0.00515747 0.00573688 -0.00684716 0.01187173 -0.01031383 0.02631155 -0.01615513 0.04570376 -0.02180505 0.06978199 -0.02703507 0.09833796 -0.03168592 0.13110429 -0.03567750 0.16777438 -0.03894575 0.20799248 -0.04146594 0.25136229 -0.04323894 0.29740143 -0.04430647 0.34555461 -0.04464846 0.39530202 -0.04420835 0.44615731 -0.04298281 0.49755498 -0.04103403 0.54885834 -0.03830858 0.59958021 -0.03466607 0.64936067 -0.03003127 0.69802270 -0.02438677 0.74557328 -0.01813550 0.79158005 -0.01209878 0.83516514 -0.00686466 0.87541871 -0.00275971 0.91143931 0.00004584 0.94236314 0.00150090 0.96729660 0.00170650 0.98543227 0.00109722 0.99635903 0.00033296 1.00000000 0.00000000 |
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Polars for MH 200 12.97% (mh200-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh200-il | 50,000 | 9 | 33.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 50,000 | 5 | 32.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 100,000 | 9 | 53.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 100,000 | 5 | 51 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 200,000 | 9 | 76.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 200,000 | 5 | 66.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 500,000 | 9 | 98.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 500,000 | 5 | 85.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 1,000,000 | 9 | 117 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 1,000,000 | 5 | 93.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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