MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 201 13.08% (mh201-il) Reynolds number: 100,000 Max Cl/Cd: 54.99 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh201-il-100000.txt Download as CSV file: xf-mh201-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 201 13.08%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4001 0.09839 0.09380 -0.0410 1.0000 0.1236
-8.750 -0.4562 0.09609 0.09174 -0.0436 1.0000 0.1266
-8.500 -0.5000 0.09406 0.08985 -0.0428 1.0000 0.1269
-8.250 -0.4413 0.09048 0.08620 -0.0370 1.0000 0.1316
-8.000 -0.4523 0.08859 0.08439 -0.0346 1.0000 0.1342
-7.750 -0.4758 0.08660 0.08251 -0.0325 1.0000 0.1365
-7.500 -0.5158 0.08453 0.08057 -0.0306 1.0000 0.1384
-7.250 -0.5836 0.08123 0.07720 -0.0339 1.0000 0.1414
-7.000 -0.5835 0.07728 0.07333 -0.0319 1.0000 0.1440
-6.750 -0.5735 0.07519 0.07130 -0.0285 1.0000 0.1475
-6.500 -0.5829 0.07222 0.06830 -0.0281 1.0000 0.1524
-5.750 -0.5727 0.04109 0.03385 -0.0372 1.0000 0.0495
-5.500 -0.5530 0.03819 0.03072 -0.0367 1.0000 0.0480
-5.250 -0.5322 0.03545 0.02764 -0.0364 1.0000 0.0471
-5.000 -0.5078 0.03344 0.02516 -0.0363 0.9995 0.0480
-4.750 -0.4699 0.03121 0.02248 -0.0385 0.9954 0.0498
-4.500 -0.4342 0.02929 0.02042 -0.0401 0.9912 0.0512
-4.250 -0.3990 0.02791 0.01896 -0.0415 0.9868 0.0537
-4.000 -0.3619 0.02697 0.01786 -0.0431 0.9825 0.0589
-3.750 -0.3305 0.02578 0.01679 -0.0443 0.9773 0.0700
-3.500 -0.2933 0.02443 0.01565 -0.0465 0.9732 0.0991
-3.250 -0.2616 0.02095 0.01502 -0.0488 0.9706 0.5344
-3.000 -0.2444 0.02163 0.01609 -0.0451 0.9632 0.6754
-2.750 -0.2238 0.02280 0.01721 -0.0420 0.9564 0.7390
-2.500 -0.2095 0.02367 0.01802 -0.0376 0.9487 0.7751
-2.250 -0.1939 0.02430 0.01854 -0.0339 0.9414 0.8032
-2.000 -0.1755 0.02474 0.01884 -0.0310 0.9340 0.8297
-1.750 -0.1638 0.02498 0.01900 -0.0268 0.9261 0.8507
-1.500 -0.1442 0.02517 0.01906 -0.0244 0.9188 0.8740
-1.250 -0.1318 0.02516 0.01897 -0.0208 0.9103 0.8940
-1.000 -0.1067 0.02519 0.01887 -0.0196 0.9033 0.9147
-0.750 -0.0847 0.02516 0.01872 -0.0184 0.8949 0.9340
-0.500 -0.0340 0.02534 0.01873 -0.0224 0.8890 0.9508
-0.250 0.0456 0.02571 0.01891 -0.0320 0.8861 0.9644
0.000 0.1043 0.02593 0.01900 -0.0387 0.8782 0.9744
0.250 0.1759 0.02597 0.01892 -0.0474 0.8734 0.9807
0.500 0.2362 0.02596 0.01881 -0.0541 0.8672 0.9868
0.750 0.2914 0.02586 0.01866 -0.0599 0.8596 0.9932
1.000 0.3611 0.02549 0.01823 -0.0679 0.8559 0.9974
1.250 0.3841 0.02549 0.01822 -0.0679 0.8440 1.0000
1.500 0.4275 0.02512 0.01782 -0.0708 0.8376 1.0000
1.750 0.4515 0.02492 0.01762 -0.0704 0.8268 1.0000
2.000 0.5173 0.02410 0.01680 -0.0768 0.8235 1.0000
2.250 0.5318 0.02398 0.01670 -0.0746 0.8108 1.0000
2.500 0.5473 0.02384 0.01658 -0.0725 0.7982 1.0000
2.750 0.6160 0.02276 0.01553 -0.0789 0.7942 1.0000
3.000 0.6304 0.02259 0.01540 -0.0764 0.7811 1.0000
3.250 0.6534 0.02222 0.01507 -0.0752 0.7691 1.0000
3.500 0.7158 0.02105 0.01394 -0.0803 0.7627 1.0000
3.750 0.7329 0.02076 0.01371 -0.0780 0.7488 1.0000
4.000 0.7534 0.02039 0.01338 -0.0762 0.7349 1.0000
4.250 0.7764 0.01998 0.01300 -0.0748 0.7208 1.0000
4.500 0.8006 0.01954 0.01261 -0.0736 0.7061 1.0000
4.750 0.8257 0.01910 0.01220 -0.0725 0.6902 1.0000
5.000 0.8528 0.01866 0.01178 -0.0718 0.6728 1.0000
5.250 0.8840 0.01821 0.01133 -0.0718 0.6541 1.0000
5.500 0.9029 0.01810 0.01125 -0.0700 0.6309 1.0000
5.750 0.9326 0.01785 0.01095 -0.0699 0.6068 1.0000
6.000 0.9573 0.01784 0.01089 -0.0691 0.5788 1.0000
6.250 0.9816 0.01798 0.01096 -0.0683 0.5483 1.0000
6.500 1.0052 0.01828 0.01113 -0.0675 0.5163 1.0000
6.750 1.0269 0.01872 0.01144 -0.0666 0.4834 1.0000
7.000 1.0469 0.01928 0.01189 -0.0654 0.4502 1.0000
7.250 1.0663 0.01993 0.01241 -0.0642 0.4180 1.0000
7.500 1.0849 0.02068 0.01300 -0.0630 0.3873 1.0000
7.750 1.1030 0.02149 0.01366 -0.0617 0.3583 1.0000
8.000 1.1205 0.02237 0.01442 -0.0605 0.3312 1.0000
8.250 1.1367 0.02328 0.01526 -0.0590 0.3054 1.0000
8.500 1.1543 0.02429 0.01611 -0.0578 0.2826 1.0000
8.750 1.1697 0.02528 0.01708 -0.0563 0.2609 1.0000
9.000 1.1859 0.02633 0.01805 -0.0549 0.2417 1.0000
9.250 1.2039 0.02749 0.01908 -0.0539 0.2242 1.0000
9.500 1.2202 0.02865 0.02020 -0.0527 0.2080 1.0000
9.750 1.2377 0.02987 0.02140 -0.0516 0.1934 1.0000
10.000 1.2545 0.03111 0.02263 -0.0505 0.1799 1.0000
10.250 1.2680 0.03232 0.02397 -0.0488 0.1680 1.0000
10.500 1.2832 0.03371 0.02545 -0.0475 0.1569 1.0000
10.750 1.3007 0.03520 0.02696 -0.0466 0.1467 1.0000
11.000 1.3237 0.03681 0.02842 -0.0466 0.1363 1.0000
11.250 1.3283 0.03820 0.03014 -0.0438 0.1289 1.0000
11.500 1.3476 0.03998 0.03192 -0.0434 0.1205 1.0000
11.750 1.3542 0.04152 0.03368 -0.0411 0.1138 1.0000
12.000 1.3711 0.04360 0.03580 -0.0405 0.1068 1.0000
12.250 1.3735 0.04537 0.03783 -0.0380 0.1014 1.0000
12.500 1.3923 0.04765 0.04007 -0.0377 0.0950 1.0000
12.750 1.3871 0.04984 0.04263 -0.0347 0.0912 1.0000
13.000 1.3910 0.05174 0.04465 -0.0329 0.0867 1.0000
13.250 1.3996 0.05465 0.04767 -0.0320 0.0824 1.0000
13.500 1.3868 0.05756 0.05097 -0.0292 0.0801 1.0000
13.750 1.3795 0.06043 0.05410 -0.0274 0.0772 1.0000
14.000 1.3850 0.06266 0.05634 -0.0266 0.0736 1.0000
14.250 1.3812 0.06674 0.06059 -0.0257 0.0712 1.0000
14.500 1.3584 0.07101 0.06524 -0.0243 0.0705 1.0000
14.750 1.3340 0.07593 0.07049 -0.0238 0.0698 1.0000
15.000 1.3079 0.08155 0.07643 -0.0243 0.0694 1.0000
15.250 1.2793 0.08797 0.08314 -0.0257 0.0694 1.0000
15.500 1.2481 0.09537 0.09081 -0.0284 0.0697 1.0000
15.750 1.2152 0.10387 0.09954 -0.0324 0.0703 1.0000
16.000 1.1817 0.11351 0.10935 -0.0377 0.0710 1.0000
16.250 1.1486 0.12426 0.12021 -0.0441 0.0718 1.0000
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Polar data table (+)
Polar graphs
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