MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 201 13.08% (mh201-il) Reynolds number: 100,000 Max Cl/Cd: 52.6 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh201-il-100000-n5.txt Download as CSV file: xf-mh201-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4133 0.09434 0.08930 -0.0507 1.0000 0.0199
-10.000 -0.4236 0.08919 0.08423 -0.0521 1.0000 0.0197
-9.750 -0.4370 0.08345 0.07858 -0.0539 1.0000 0.0191
-9.500 -0.4624 0.07471 0.06989 -0.0581 1.0000 0.0185
-9.250 -0.4983 0.06829 0.06346 -0.0601 1.0000 0.0180
-9.000 -0.5360 0.06466 0.05980 -0.0583 1.0000 0.0178
-8.500 -0.5833 0.05388 0.04828 -0.0615 0.9873 0.0170
-8.250 -0.5755 0.04933 0.04332 -0.0640 0.9798 0.0169
-8.000 -0.5620 0.04538 0.03894 -0.0659 0.9733 0.0169
-7.750 -0.5477 0.04194 0.03507 -0.0667 0.9664 0.0169
-7.500 -0.5277 0.03844 0.03101 -0.0678 0.9611 0.0170
-7.250 -0.5067 0.03580 0.02803 -0.0683 0.9559 0.0172
-7.000 -0.4839 0.03364 0.02557 -0.0687 0.9506 0.0175
-6.750 -0.4554 0.03187 0.02361 -0.0700 0.9470 0.0185
-6.500 -0.4309 0.03031 0.02180 -0.0701 0.9420 0.0193
-6.250 -0.4049 0.02882 0.01995 -0.0702 0.9370 0.0214
-6.000 -0.3755 0.02739 0.01847 -0.0712 0.9336 0.0226
-5.750 -0.3443 0.02607 0.01702 -0.0722 0.9308 0.0240
-5.500 -0.3239 0.02502 0.01584 -0.0711 0.9240 0.0256
-5.250 -0.2951 0.02388 0.01464 -0.0719 0.9201 0.0277
-5.000 -0.2624 0.02291 0.01358 -0.0733 0.9173 0.0333
-4.750 -0.2398 0.02211 0.01272 -0.0728 0.9110 0.0394
-4.500 -0.2113 0.02114 0.01181 -0.0735 0.9064 0.0534
-4.250 -0.1796 0.01982 0.01091 -0.0750 0.9034 0.1145
-4.000 -0.1486 0.01856 0.01033 -0.0768 0.9005 0.2506
-3.750 -0.1286 0.01767 0.01010 -0.0763 0.8935 0.3878
-3.500 -0.1024 0.01708 0.01024 -0.0757 0.8896 0.5417
-3.250 -0.0725 0.01718 0.01050 -0.0750 0.8868 0.6226
-3.000 -0.0524 0.01744 0.01070 -0.0730 0.8795 0.6620
-2.750 -0.0227 0.01762 0.01074 -0.0728 0.8750 0.6929
-2.500 0.0113 0.01774 0.01071 -0.0734 0.8720 0.7168
-2.250 0.0340 0.01793 0.01078 -0.0722 0.8653 0.7348
-2.000 0.0613 0.01806 0.01080 -0.0716 0.8601 0.7500
-1.750 0.0931 0.01810 0.01073 -0.0717 0.8566 0.7632
-1.500 0.1142 0.01824 0.01079 -0.0700 0.8497 0.7750
-1.250 0.1412 0.01828 0.01075 -0.0694 0.8442 0.7872
-1.000 0.1744 0.01823 0.01059 -0.0700 0.8407 0.7996
-0.750 0.1922 0.01833 0.01066 -0.0677 0.8325 0.8090
-0.500 0.2223 0.01825 0.01050 -0.0678 0.8274 0.8177
-0.250 0.2555 0.01811 0.01029 -0.0685 0.8232 0.8253
0.000 0.2754 0.01814 0.01029 -0.0670 0.8142 0.8328
0.250 0.3094 0.01797 0.01005 -0.0678 0.8097 0.8392
0.500 0.3310 0.01798 0.01004 -0.0666 0.8008 0.8465
0.750 0.3623 0.01781 0.00983 -0.0669 0.7951 0.8523
1.000 0.3873 0.01779 0.00978 -0.0665 0.7864 0.8596
1.250 0.4171 0.01760 0.00958 -0.0664 0.7796 0.8646
1.500 0.4405 0.01756 0.00954 -0.0655 0.7704 0.8708
1.750 0.4740 0.01737 0.00932 -0.0664 0.7632 0.8759
2.000 0.4954 0.01732 0.00930 -0.0650 0.7526 0.8813
2.250 0.5270 0.01716 0.00912 -0.0656 0.7442 0.8862
2.500 0.5530 0.01707 0.00904 -0.0651 0.7333 0.8914
2.750 0.5763 0.01699 0.00900 -0.0641 0.7216 0.8966
3.000 0.6038 0.01689 0.00891 -0.0640 0.7102 0.9019
3.250 0.6322 0.01676 0.00879 -0.0639 0.6983 0.9066
3.500 0.6574 0.01666 0.00872 -0.0632 0.6848 0.9120
3.750 0.6820 0.01660 0.00869 -0.0626 0.6698 0.9179
4.000 0.7070 0.01652 0.00865 -0.0619 0.6538 0.9233
4.250 0.7303 0.01649 0.00865 -0.0610 0.6357 0.9299
4.500 0.7547 0.01647 0.00865 -0.0603 0.6164 0.9364
4.750 0.7811 0.01645 0.00863 -0.0599 0.5957 0.9432
5.000 0.8076 0.01648 0.00865 -0.0597 0.5726 0.9503
5.250 0.8350 0.01658 0.00870 -0.0596 0.5477 0.9586
5.500 0.8632 0.01678 0.00887 -0.0599 0.5202 0.9684
6.000 0.9148 0.01739 0.00933 -0.0599 0.4625 1.0000
6.250 0.9368 0.01785 0.00970 -0.0593 0.4343 1.0000
6.500 0.9581 0.01837 0.01011 -0.0587 0.4067 1.0000
6.750 0.9788 0.01893 0.01059 -0.0580 0.3793 1.0000
7.000 0.9988 0.01952 0.01111 -0.0572 0.3536 1.0000
7.250 1.0172 0.02017 0.01168 -0.0562 0.3293 1.0000
7.500 1.0357 0.02082 0.01229 -0.0552 0.3061 1.0000
7.750 1.0529 0.02156 0.01295 -0.0541 0.2847 1.0000
8.000 1.0705 0.02230 0.01366 -0.0530 0.2643 1.0000
8.250 1.0872 0.02309 0.01444 -0.0519 0.2453 1.0000
8.500 1.1032 0.02392 0.01524 -0.0506 0.2279 1.0000
8.750 1.1186 0.02479 0.01610 -0.0494 0.2118 1.0000
9.000 1.1335 0.02571 0.01701 -0.0481 0.1970 1.0000
9.250 1.1479 0.02666 0.01799 -0.0468 0.1832 1.0000
9.500 1.1620 0.02765 0.01901 -0.0455 0.1708 1.0000
9.750 1.1752 0.02870 0.02009 -0.0442 0.1594 1.0000
10.000 1.1868 0.02986 0.02124 -0.0427 0.1493 1.0000
10.250 1.1993 0.03100 0.02245 -0.0414 0.1394 1.0000
10.500 1.2113 0.03220 0.02375 -0.0402 0.1305 1.0000
10.750 1.2201 0.03360 0.02514 -0.0387 0.1229 1.0000
11.000 1.2324 0.03487 0.02655 -0.0376 0.1150 1.0000
11.250 1.2401 0.03642 0.02809 -0.0363 0.1088 1.0000
11.500 1.2509 0.03784 0.02969 -0.0352 0.1017 1.0000
11.750 1.2568 0.03959 0.03144 -0.0339 0.0965 1.0000
12.000 1.2665 0.04119 0.03324 -0.0329 0.0905 1.0000
12.250 1.2722 0.04304 0.03517 -0.0319 0.0856 1.0000
12.500 1.2785 0.04499 0.03722 -0.0309 0.0812 1.0000
12.750 1.2843 0.04698 0.03938 -0.0301 0.0764 1.0000
13.000 1.2871 0.04924 0.04168 -0.0294 0.0729 1.0000
13.250 1.2917 0.05153 0.04415 -0.0287 0.0691 1.0000
13.500 1.2947 0.05397 0.04676 -0.0282 0.0653 1.0000
13.750 1.2951 0.05664 0.04952 -0.0279 0.0623 1.0000
14.000 1.2957 0.05949 0.05250 -0.0276 0.0596 1.0000
14.250 1.2961 0.06250 0.05575 -0.0275 0.0566 1.0000
14.500 1.2945 0.06573 0.05913 -0.0278 0.0540 1.0000
14.750 1.2915 0.06918 0.06267 -0.0283 0.0518 1.0000
15.000 1.2886 0.07288 0.06650 -0.0289 0.0499 1.0000
15.250 1.2840 0.07702 0.07091 -0.0298 0.0478 1.0000
15.500 1.2783 0.08139 0.07548 -0.0311 0.0458 1.0000
15.750 1.2722 0.08590 0.08013 -0.0327 0.0442 1.0000
16.000 1.2663 0.09048 0.08481 -0.0345 0.0428 1.0000
16.250 1.2599 0.09532 0.08975 -0.0364 0.0415 1.0000
16.500 1.2477 0.10153 0.09626 -0.0393 0.0404 1.0000
16.750 1.2345 0.10815 0.10313 -0.0427 0.0393 1.0000
17.000 1.2202 0.11522 0.11042 -0.0466 0.0384 1.0000
17.250 1.2045 0.12280 0.11820 -0.0511 0.0377 1.0000
17.500 1.1868 0.13113 0.12673 -0.0562 0.0371 1.0000
17.750 1.1621 0.14161 0.13742 -0.0629 0.0370 1.0000
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Polar data table (+)
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