MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 201 13.08% (mh201-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.58 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh201-il-1000000.txt Download as CSV file: xf-mh201-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3041 0.12593 0.12438 -0.0378 1.0000 0.0090
-12.500 -0.3041 0.12226 0.12072 -0.0389 0.9998 0.0093
-12.250 -0.4041 0.12407 0.12236 -0.0370 1.0000 0.0087
-12.000 -0.4051 0.11990 0.11820 -0.0380 1.0000 0.0086
-11.750 -0.4057 0.11618 0.11451 -0.0388 1.0000 0.0088
-8.500 -0.4664 0.02201 0.01778 -0.1009 0.9595 0.0080
-8.250 -0.4460 0.01971 0.01538 -0.1005 0.9518 0.0075
-8.000 -0.4155 0.01777 0.01322 -0.1021 0.9480 0.0074
-7.750 -0.3831 0.01654 0.01183 -0.1037 0.9439 0.0075
-7.500 -0.3538 0.01531 0.01044 -0.1046 0.9366 0.0075
-7.250 -0.3205 0.01416 0.00916 -0.1062 0.9311 0.0075
-7.000 -0.2937 0.01319 0.00808 -0.1065 0.9210 0.0074
-6.750 -0.2666 0.01233 0.00711 -0.1067 0.9117 0.0073
-6.500 -0.2399 0.01168 0.00636 -0.1069 0.9020 0.0073
-6.250 -0.2156 0.01109 0.00568 -0.1064 0.8918 0.0074
-6.000 -0.1900 0.01062 0.00512 -0.1062 0.8830 0.0074
-5.750 -0.1646 0.01020 0.00462 -0.1059 0.8741 0.0075
-5.500 -0.1386 0.00983 0.00418 -0.1057 0.8662 0.0077
-5.250 -0.1124 0.00951 0.00379 -0.1055 0.8585 0.0079
-5.000 -0.0864 0.00910 0.00330 -0.1053 0.8516 0.0089
-4.750 -0.0597 0.00882 0.00297 -0.1052 0.8446 0.0112
-4.500 -0.0331 0.00841 0.00262 -0.1051 0.8383 0.0293
-4.250 -0.0069 0.00798 0.00238 -0.1051 0.8319 0.0711
-4.000 0.0199 0.00762 0.00217 -0.1053 0.8258 0.1203
-3.750 0.0470 0.00726 0.00201 -0.1055 0.8200 0.1772
-3.500 0.0740 0.00679 0.00184 -0.1058 0.8139 0.2651
-3.250 0.1013 0.00620 0.00166 -0.1063 0.8081 0.3935
-3.000 0.1293 0.00585 0.00155 -0.1067 0.8022 0.4709
-2.750 0.1576 0.00552 0.00146 -0.1071 0.7963 0.5583
-2.500 0.1861 0.00539 0.00145 -0.1073 0.7908 0.6117
-2.250 0.2146 0.00534 0.00144 -0.1074 0.7848 0.6417
-2.000 0.2431 0.00536 0.00145 -0.1075 0.7789 0.6621
-1.750 0.2717 0.00538 0.00146 -0.1076 0.7731 0.6769
-1.500 0.3003 0.00542 0.00146 -0.1077 0.7669 0.6886
-1.250 0.3286 0.00547 0.00149 -0.1077 0.7609 0.6975
-1.000 0.3571 0.00549 0.00149 -0.1078 0.7544 0.7057
-0.750 0.3852 0.00555 0.00152 -0.1078 0.7477 0.7123
-0.500 0.4137 0.00559 0.00154 -0.1079 0.7409 0.7189
-0.250 0.4417 0.00563 0.00156 -0.1079 0.7336 0.7242
0.000 0.4698 0.00568 0.00159 -0.1079 0.7264 0.7294
0.250 0.4979 0.00575 0.00161 -0.1079 0.7182 0.7347
0.500 0.5257 0.00579 0.00165 -0.1079 0.7100 0.7399
0.750 0.5530 0.00586 0.00170 -0.1077 0.7006 0.7451
1.000 0.5810 0.00592 0.00174 -0.1077 0.6905 0.7496
1.250 0.6085 0.00598 0.00177 -0.1076 0.6796 0.7531
1.500 0.6353 0.00604 0.00181 -0.1074 0.6669 0.7563
1.750 0.6620 0.00613 0.00185 -0.1072 0.6514 0.7595
2.000 0.6886 0.00624 0.00191 -0.1069 0.6338 0.7628
2.250 0.7146 0.00638 0.00198 -0.1065 0.6128 0.7659
2.500 0.7398 0.00654 0.00205 -0.1060 0.5891 0.7691
2.750 0.7644 0.00673 0.00216 -0.1054 0.5641 0.7724
3.000 0.7891 0.00695 0.00228 -0.1048 0.5381 0.7758
3.250 0.8135 0.00719 0.00243 -0.1042 0.5112 0.7789
3.500 0.8379 0.00746 0.00257 -0.1036 0.4835 0.7817
3.750 0.8621 0.00772 0.00272 -0.1030 0.4548 0.7841
4.000 0.8860 0.00797 0.00288 -0.1023 0.4268 0.7866
4.250 0.9097 0.00825 0.00306 -0.1017 0.3995 0.7891
4.500 0.9334 0.00855 0.00325 -0.1010 0.3739 0.7916
4.750 0.9569 0.00886 0.00346 -0.1003 0.3470 0.7942
5.000 0.9808 0.00916 0.00366 -0.0997 0.3235 0.7967
5.250 1.0039 0.00949 0.00388 -0.0989 0.2993 0.7989
5.500 1.0272 0.00977 0.00410 -0.0982 0.2778 0.8016
5.750 1.0502 0.01007 0.00434 -0.0975 0.2577 0.8041
6.000 1.0728 0.01041 0.00459 -0.0966 0.2380 0.8067
6.250 1.0956 0.01073 0.00485 -0.0959 0.2196 0.8093
6.500 1.1181 0.01107 0.00512 -0.0951 0.2017 0.8121
6.750 1.1405 0.01140 0.00539 -0.0942 0.1861 0.8146
7.000 1.1623 0.01173 0.00568 -0.0933 0.1716 0.8174
7.250 1.1836 0.01207 0.00599 -0.0923 0.1574 0.8202
7.500 1.2048 0.01243 0.00631 -0.0912 0.1443 0.8233
7.750 1.2255 0.01281 0.00664 -0.0901 0.1318 0.8265
8.000 1.2451 0.01320 0.00698 -0.0888 0.1206 0.8296
8.250 1.2631 0.01356 0.00733 -0.0872 0.1107 0.8330
8.500 1.2819 0.01389 0.00767 -0.0857 0.1029 0.8365
8.750 1.2997 0.01431 0.00807 -0.0841 0.0945 0.8405
9.000 1.3175 0.01474 0.00847 -0.0825 0.0870 0.8445
9.250 1.3352 0.01512 0.00890 -0.0809 0.0805 0.8489
9.500 1.3512 0.01562 0.00937 -0.0791 0.0731 0.8537
9.750 1.3694 0.01602 0.00981 -0.0776 0.0683 0.8586
10.000 1.3842 0.01657 0.01034 -0.0757 0.0617 0.8641
10.250 1.4012 0.01700 0.01082 -0.0741 0.0576 0.8706
10.500 1.4152 0.01760 0.01142 -0.0722 0.0519 0.8779
10.750 1.4307 0.01809 0.01196 -0.0705 0.0477 0.8868
11.000 1.4430 0.01873 0.01262 -0.0683 0.0430 0.8977
11.250 1.4564 0.01925 0.01322 -0.0663 0.0402 0.9134
11.500 1.4643 0.01971 0.01381 -0.0632 0.0373 1.0000
11.750 1.4779 0.02051 0.01461 -0.0617 0.0336 1.0000
12.000 1.4923 0.02126 0.01539 -0.0603 0.0309 1.0000
12.250 1.5035 0.02223 0.01634 -0.0586 0.0275 1.0000
12.500 1.5170 0.02305 0.01720 -0.0572 0.0252 1.0000
12.750 1.5269 0.02413 0.01828 -0.0554 0.0225 1.0000
13.000 1.5390 0.02508 0.01928 -0.0540 0.0209 1.0000
13.250 1.5491 0.02620 0.02042 -0.0525 0.0190 1.0000
13.500 1.5580 0.02743 0.02171 -0.0510 0.0174 1.0000
13.750 1.5681 0.02860 0.02293 -0.0496 0.0162 1.0000
14.000 1.5759 0.02999 0.02435 -0.0482 0.0148 1.0000
14.250 1.5830 0.03147 0.02589 -0.0468 0.0137 1.0000
14.500 1.5913 0.03289 0.02738 -0.0457 0.0129 1.0000
14.750 1.5974 0.03455 0.02909 -0.0445 0.0118 1.0000
15.000 1.6014 0.03644 0.03103 -0.0433 0.0108 1.0000
15.250 1.6078 0.03817 0.03284 -0.0424 0.0102 1.0000
15.500 1.6123 0.04014 0.03489 -0.0415 0.0094 1.0000
15.750 1.6147 0.04238 0.03720 -0.0407 0.0088 1.0000
16.000 1.6163 0.04479 0.03968 -0.0400 0.0081 1.0000
16.250 1.6193 0.04714 0.04212 -0.0396 0.0076 1.0000
16.500 1.6198 0.04987 0.04492 -0.0393 0.0069 1.0000
16.750 1.6178 0.05298 0.04811 -0.0392 0.0064 1.0000
17.000 1.6165 0.05612 0.05136 -0.0393 0.0059 1.0000
17.250 1.6147 0.05948 0.05482 -0.0396 0.0055 1.0000
17.500 1.6105 0.06330 0.05873 -0.0403 0.0050 1.0000
17.750 1.6022 0.06785 0.06337 -0.0413 0.0044 1.0000
18.000 1.5968 0.07215 0.06780 -0.0425 0.0042 1.0000
18.250 1.5872 0.07728 0.07303 -0.0442 0.0035 1.0000
18.500 1.5721 0.08349 0.07936 -0.0465 0.0030 1.0000
18.750 1.5610 0.08922 0.08523 -0.0489 0.0028 1.0000
19.000 1.5471 0.09565 0.09180 -0.0518 0.0026 1.0000
19.250 1.5304 0.10277 0.09907 -0.0552 0.0024 1.0000
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Polar data table (+)
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