MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 200 12.97% (mh200-il) Reynolds number: 200,000 Max Cl/Cd: 66.65 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh200-il-200000-n5.txt Download as CSV file: xf-mh200-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 200 12.97%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4466 0.08557 0.08205 -0.0556 1.0000 0.0110
-10.500 -0.4595 0.07793 0.07445 -0.0592 1.0000 0.0107
-10.250 -0.4836 0.06803 0.06452 -0.0657 1.0000 0.0105
-10.000 -0.5083 0.06235 0.05881 -0.0684 1.0000 0.0104
-9.750 -0.5306 0.05754 0.05391 -0.0704 0.9974 0.0103
-9.500 -0.5390 0.05148 0.04757 -0.0762 0.9837 0.0101
-9.250 -0.5456 0.04678 0.04257 -0.0787 0.9669 0.0100
-9.000 -0.5432 0.04190 0.03727 -0.0805 0.9546 0.0098
-8.750 -0.5358 0.03747 0.03235 -0.0814 0.9440 0.0096
-8.500 -0.5233 0.03385 0.02823 -0.0816 0.9344 0.0094
-8.250 -0.5038 0.03060 0.02450 -0.0821 0.9280 0.0094
-8.000 -0.4847 0.02812 0.02161 -0.0818 0.9198 0.0094
-7.750 -0.4599 0.02596 0.01909 -0.0822 0.9145 0.0094
-7.500 -0.4374 0.02423 0.01709 -0.0818 0.9074 0.0095
-7.250 -0.4118 0.02270 0.01534 -0.0819 0.9019 0.0096
-7.000 -0.3874 0.02139 0.01385 -0.0817 0.8960 0.0099
-6.750 -0.3639 0.02027 0.01258 -0.0812 0.8898 0.0102
-6.500 -0.3393 0.01922 0.01138 -0.0810 0.8852 0.0106
-6.250 -0.3183 0.01837 0.01043 -0.0801 0.8789 0.0111
-6.000 -0.2954 0.01760 0.00954 -0.0795 0.8738 0.0116
-5.750 -0.2732 0.01675 0.00859 -0.0790 0.8692 0.0126
-5.500 -0.2506 0.01622 0.00800 -0.0783 0.8635 0.0148
-5.250 -0.2268 0.01564 0.00732 -0.0779 0.8590 0.0181
-5.000 -0.2020 0.01506 0.00664 -0.0775 0.8555 0.0240
-4.750 -0.1809 0.01432 0.00606 -0.0767 0.8504 0.0512
-4.500 -0.1603 0.01339 0.00557 -0.0762 0.8459 0.1401
-4.250 -0.1391 0.01245 0.00517 -0.0758 0.8423 0.2646
-4.000 -0.1191 0.01163 0.00489 -0.0752 0.8380 0.3918
-3.750 -0.0973 0.01108 0.00475 -0.0744 0.8337 0.4974
-3.500 -0.0731 0.01081 0.00476 -0.0736 0.8302 0.5761
-3.250 -0.0466 0.01078 0.00479 -0.0731 0.8273 0.6264
-3.000 -0.0212 0.01084 0.00486 -0.0724 0.8232 0.6584
-2.750 0.0054 0.01092 0.00489 -0.0720 0.8193 0.6826
-2.500 0.0328 0.01099 0.00489 -0.0718 0.8159 0.7008
-2.250 0.0610 0.01107 0.00487 -0.0718 0.8130 0.7156
-2.000 0.0873 0.01115 0.00489 -0.0714 0.8089 0.7285
-1.750 0.1137 0.01124 0.00494 -0.0711 0.8048 0.7389
-1.500 0.1412 0.01131 0.00495 -0.0709 0.8013 0.7482
-1.250 0.1697 0.01136 0.00491 -0.0710 0.7984 0.7581
-1.000 0.1947 0.01146 0.00502 -0.0703 0.7938 0.7664
-0.750 0.2212 0.01154 0.00507 -0.0700 0.7896 0.7750
-0.500 0.2487 0.01159 0.00507 -0.0698 0.7860 0.7823
-0.250 0.2763 0.01162 0.00507 -0.0697 0.7822 0.7885
0.000 0.3016 0.01168 0.00514 -0.0692 0.7768 0.7937
0.250 0.3296 0.01169 0.00510 -0.0693 0.7721 0.7997
0.500 0.3567 0.01170 0.00510 -0.0691 0.7675 0.8042
0.750 0.3821 0.01173 0.00515 -0.0686 0.7613 0.8091
1.000 0.4107 0.01172 0.00511 -0.0687 0.7562 0.8147
1.250 0.4358 0.01175 0.00517 -0.0681 0.7499 0.8189
1.500 0.4623 0.01175 0.00518 -0.0678 0.7435 0.8235
1.750 0.4894 0.01175 0.00517 -0.0677 0.7368 0.8285
2.000 0.5155 0.01172 0.00517 -0.0673 0.7290 0.8323
2.250 0.5409 0.01171 0.00520 -0.0668 0.7205 0.8360
2.500 0.5682 0.01168 0.00516 -0.0666 0.7123 0.8401
2.750 0.5940 0.01168 0.00521 -0.0663 0.7021 0.8445
3.000 0.6191 0.01167 0.00525 -0.0657 0.6924 0.8477
3.250 0.6450 0.01165 0.00526 -0.0653 0.6819 0.8513
3.500 0.6704 0.01165 0.00530 -0.0648 0.6695 0.8555
3.750 0.6957 0.01165 0.00534 -0.0644 0.6551 0.8595
4.000 0.7193 0.01166 0.00541 -0.0634 0.6378 0.8629
4.250 0.7431 0.01168 0.00544 -0.0626 0.6163 0.8670
4.500 0.7672 0.01174 0.00546 -0.0618 0.5889 0.8715
4.750 0.7890 0.01188 0.00551 -0.0606 0.5569 0.8754
5.000 0.8085 0.01213 0.00563 -0.0590 0.5208 0.8799
5.250 0.8270 0.01249 0.00583 -0.0573 0.4822 0.8852
5.500 0.8435 0.01289 0.00609 -0.0553 0.4435 0.8901
5.750 0.8588 0.01334 0.00641 -0.0531 0.4060 0.8959
6.000 0.8742 0.01382 0.00679 -0.0511 0.3706 0.9025
6.250 0.8879 0.01430 0.00716 -0.0487 0.3375 0.9094
6.500 0.9024 0.01480 0.00756 -0.0466 0.3058 0.9172
6.750 0.9158 0.01529 0.00797 -0.0442 0.2773 0.9270
7.000 0.9290 0.01577 0.00840 -0.0419 0.2511 0.9395
7.500 0.9662 0.01689 0.00943 -0.0400 0.2005 1.0000
7.750 0.9835 0.01756 0.01002 -0.0389 0.1793 1.0000
8.000 1.0007 0.01824 0.01065 -0.0379 0.1592 1.0000
8.500 1.0332 0.01972 0.01201 -0.0356 0.1227 1.0000
8.750 1.0486 0.02052 0.01279 -0.0343 0.1060 1.0000
9.000 1.0633 0.02137 0.01360 -0.0330 0.0912 1.0000
9.250 1.0777 0.02224 0.01446 -0.0317 0.0788 1.0000
9.500 1.0916 0.02317 0.01539 -0.0304 0.0682 1.0000
9.750 1.1047 0.02416 0.01639 -0.0291 0.0591 1.0000
10.250 1.1295 0.02629 0.01859 -0.0263 0.0460 1.0000
10.500 1.1390 0.02759 0.01993 -0.0248 0.0409 1.0000
10.750 1.1511 0.02872 0.02117 -0.0236 0.0371 1.0000
11.000 1.1613 0.03000 0.02251 -0.0223 0.0334 1.0000
11.250 1.1682 0.03158 0.02414 -0.0208 0.0305 1.0000
11.500 1.1792 0.03286 0.02555 -0.0198 0.0278 1.0000
11.750 1.1880 0.03434 0.02713 -0.0186 0.0254 1.0000
12.000 1.1927 0.03619 0.02904 -0.0174 0.0234 1.0000
12.250 1.1990 0.03797 0.03095 -0.0162 0.0216 1.0000
12.500 1.2068 0.03964 0.03276 -0.0154 0.0197 1.0000
12.750 1.2130 0.04148 0.03470 -0.0146 0.0180 1.0000
13.000 1.2130 0.04395 0.03727 -0.0137 0.0166 1.0000
13.250 1.2171 0.04614 0.03962 -0.0130 0.0154 1.0000
13.500 1.2215 0.04834 0.04197 -0.0125 0.0139 1.0000
13.750 1.2232 0.05087 0.04463 -0.0122 0.0129 1.0000
14.000 1.2219 0.05382 0.04767 -0.0121 0.0119 1.0000
14.250 1.2192 0.05709 0.05109 -0.0120 0.0111 1.0000
14.500 1.2190 0.06020 0.05439 -0.0123 0.0102 1.0000
14.750 1.2162 0.06377 0.05812 -0.0128 0.0096 1.0000
15.000 1.2140 0.06741 0.06190 -0.0137 0.0088 1.0000
15.250 1.2087 0.07166 0.06629 -0.0150 0.0085 1.0000
15.500 1.2002 0.07660 0.07138 -0.0167 0.0082 1.0000
15.750 1.1884 0.08233 0.07726 -0.0190 0.0079 1.0000
16.000 1.1793 0.08785 0.08297 -0.0213 0.0077 1.0000
16.250 1.1691 0.09384 0.08916 -0.0241 0.0075 1.0000
16.500 1.1578 0.10023 0.09574 -0.0272 0.0074 1.0000
16.750 1.1454 0.10706 0.10275 -0.0308 0.0072 1.0000
17.000 1.1330 0.11412 0.11000 -0.0347 0.0070 1.0000
17.250 1.1194 0.12161 0.11765 -0.0389 0.0070 1.0000
17.500 1.1054 0.12949 0.12570 -0.0435 0.0069 1.0000
17.750 1.0913 0.13757 0.13394 -0.0483 0.0069 1.0000
18.000 1.0768 0.14599 0.14250 -0.0534 0.0069 1.0000
18.250 1.0619 0.15481 0.15147 -0.0587 0.0069 1.0000
18.500 1.0454 0.16441 0.16120 -0.0646 0.0070 1.0000
18.750 1.0269 0.17507 0.17198 -0.0709 0.0071 1.0000
19.000 1.0027 0.18819 0.18521 -0.0784 0.0074 1.0000
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Polar data table (+)
Polar graphs
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