MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 201 13.08% (mh201-il) Reynolds number: 200,000 Max Cl/Cd: 67.05 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh201-il-200000-n5.txt Download as CSV file: xf-mh201-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4204 0.09388 0.09029 -0.0488 1.0000 0.0122
-10.250 -0.4985 0.06791 0.06425 -0.0621 1.0000 0.0104
-10.000 -0.5261 0.06213 0.05842 -0.0645 1.0000 0.0104
-9.500 -0.5503 0.05186 0.04782 -0.0735 0.9904 0.0102
-9.250 -0.5538 0.04747 0.04317 -0.0774 0.9808 0.0102
-9.000 -0.5487 0.04272 0.03804 -0.0806 0.9721 0.0101
-8.750 -0.5430 0.03898 0.03391 -0.0813 0.9625 0.0100
-8.500 -0.5300 0.03548 0.03000 -0.0823 0.9558 0.0100
-8.250 -0.5141 0.03228 0.02636 -0.0827 0.9492 0.0100
-8.000 -0.4895 0.02952 0.02318 -0.0841 0.9459 0.0100
-7.750 -0.4708 0.02747 0.02082 -0.0835 0.9386 0.0100
-7.500 -0.4443 0.02540 0.01840 -0.0841 0.9348 0.0102
-7.250 -0.4145 0.02369 0.01641 -0.0852 0.9324 0.0103
-7.000 -0.3895 0.02237 0.01493 -0.0852 0.9272 0.0105
-6.750 -0.3630 0.02111 0.01361 -0.0856 0.9224 0.0109
-6.500 -0.3317 0.02003 0.01244 -0.0869 0.9193 0.0112
-6.250 -0.2990 0.01900 0.01131 -0.0884 0.9169 0.0121
-6.000 -0.2747 0.01821 0.01043 -0.0882 0.9106 0.0126
-5.750 -0.2450 0.01739 0.00950 -0.0890 0.9062 0.0136
-5.500 -0.2123 0.01669 0.00876 -0.0905 0.9030 0.0162
-5.250 -0.1827 0.01605 0.00806 -0.0913 0.8985 0.0188
-5.000 -0.1552 0.01542 0.00736 -0.0915 0.8926 0.0230
-4.750 -0.1234 0.01470 0.00665 -0.0927 0.8886 0.0346
-4.500 -0.0923 0.01386 0.00603 -0.0940 0.8847 0.0760
-4.250 -0.0676 0.01308 0.00564 -0.0942 0.8779 0.1581
-4.000 -0.0373 0.01229 0.00525 -0.0955 0.8733 0.2554
-3.750 -0.0071 0.01156 0.00491 -0.0967 0.8688 0.3640
-3.500 0.0184 0.01096 0.00477 -0.0967 0.8623 0.4776
-3.250 0.0477 0.01067 0.00475 -0.0970 0.8576 0.5603
-3.000 0.0760 0.01063 0.00481 -0.0968 0.8525 0.6138
-2.750 0.1026 0.01069 0.00488 -0.0962 0.8462 0.6473
-2.500 0.1333 0.01074 0.00486 -0.0965 0.8414 0.6722
-2.250 0.1614 0.01083 0.00487 -0.0964 0.8356 0.6899
-2.000 0.1895 0.01090 0.00487 -0.0963 0.8294 0.7046
-1.750 0.2198 0.01096 0.00486 -0.0965 0.8245 0.7159
-1.500 0.2454 0.01105 0.00491 -0.0959 0.8174 0.7259
-1.250 0.2750 0.01110 0.00486 -0.0961 0.8112 0.7364
-1.000 0.3016 0.01118 0.00492 -0.0956 0.8047 0.7443
-0.750 0.3289 0.01125 0.00493 -0.0953 0.7975 0.7537
-0.500 0.3568 0.01131 0.00495 -0.0951 0.7913 0.7609
-0.250 0.3837 0.01135 0.00495 -0.0949 0.7832 0.7682
0.000 0.4117 0.01138 0.00494 -0.0946 0.7765 0.7727
0.250 0.4373 0.01142 0.00496 -0.0941 0.7678 0.7782
0.500 0.4668 0.01144 0.00491 -0.0944 0.7603 0.7837
0.750 0.4916 0.01147 0.00496 -0.0937 0.7509 0.7877
1.000 0.5184 0.01150 0.00496 -0.0933 0.7420 0.7925
1.250 0.5467 0.01153 0.00494 -0.0934 0.7324 0.7980
1.500 0.5715 0.01156 0.00499 -0.0927 0.7217 0.8018
1.750 0.5975 0.01159 0.00501 -0.0922 0.7111 0.8057
2.000 0.6246 0.01162 0.00500 -0.0920 0.6996 0.8100
2.250 0.6513 0.01166 0.00502 -0.0918 0.6863 0.8143
2.500 0.6757 0.01169 0.00507 -0.0910 0.6721 0.8172
2.750 0.7006 0.01174 0.00511 -0.0903 0.6564 0.8205
3.000 0.7260 0.01181 0.00514 -0.0898 0.6389 0.8242
3.250 0.7516 0.01190 0.00518 -0.0894 0.6188 0.8280
3.500 0.7756 0.01202 0.00525 -0.0886 0.5965 0.8311
3.750 0.7984 0.01217 0.00533 -0.0875 0.5730 0.8342
4.000 0.8209 0.01238 0.00544 -0.0865 0.5477 0.8376
4.250 0.8435 0.01262 0.00561 -0.0855 0.5209 0.8415
4.500 0.8656 0.01291 0.00579 -0.0846 0.4933 0.8452
4.750 0.8852 0.01321 0.00600 -0.0830 0.4663 0.8483
5.000 0.9044 0.01356 0.00626 -0.0815 0.4386 0.8521
5.250 0.9244 0.01392 0.00654 -0.0802 0.4114 0.8563
5.500 0.9444 0.01431 0.00684 -0.0789 0.3849 0.8602
5.750 0.9618 0.01470 0.00715 -0.0771 0.3607 0.8638
6.000 0.9801 0.01510 0.00750 -0.0756 0.3364 0.8682
6.250 0.9985 0.01554 0.00788 -0.0741 0.3141 0.8731
6.500 1.0162 0.01596 0.00825 -0.0725 0.2924 0.8773
6.750 1.0324 0.01639 0.00864 -0.0706 0.2724 0.8821
7.250 1.0638 0.01729 0.00949 -0.0667 0.2368 0.8938
7.500 1.0795 0.01776 0.00995 -0.0648 0.2205 0.9005
7.750 1.0948 0.01826 0.01044 -0.0629 0.2051 0.9076
8.000 1.1094 0.01876 0.01096 -0.0609 0.1910 0.9167
8.250 1.1227 0.01927 0.01148 -0.0587 0.1781 0.9290
8.500 1.1366 0.01979 0.01202 -0.0567 0.1655 0.9490
8.750 1.1541 0.02035 0.01260 -0.0557 0.1530 1.0000
9.000 1.1726 0.02107 0.01334 -0.0549 0.1416 1.0000
9.250 1.1898 0.02183 0.01411 -0.0539 0.1312 1.0000
9.500 1.2055 0.02268 0.01495 -0.0528 0.1219 1.0000
9.750 1.2219 0.02349 0.01578 -0.0518 0.1129 1.0000
10.000 1.2369 0.02437 0.01671 -0.0506 0.1052 1.0000
10.250 1.2506 0.02534 0.01769 -0.0494 0.0978 1.0000
10.500 1.2651 0.02626 0.01868 -0.0482 0.0913 1.0000
10.750 1.2771 0.02736 0.01979 -0.0469 0.0851 1.0000
11.000 1.2902 0.02840 0.02092 -0.0457 0.0797 1.0000
11.250 1.3017 0.02957 0.02213 -0.0444 0.0744 1.0000
11.500 1.3121 0.03085 0.02348 -0.0432 0.0700 1.0000
11.750 1.3235 0.03207 0.02480 -0.0420 0.0653 1.0000
12.000 1.3310 0.03361 0.02637 -0.0408 0.0613 1.0000
12.250 1.3415 0.03497 0.02785 -0.0397 0.0575 1.0000
12.500 1.3499 0.03651 0.02947 -0.0387 0.0536 1.0000
12.750 1.3547 0.03841 0.03140 -0.0376 0.0505 1.0000
13.000 1.3634 0.04001 0.03318 -0.0367 0.0474 1.0000
13.250 1.3694 0.04191 0.03516 -0.0359 0.0444 1.0000
13.500 1.3713 0.04423 0.03753 -0.0351 0.0420 1.0000
13.750 1.3768 0.04628 0.03974 -0.0344 0.0397 1.0000
14.000 1.3808 0.04855 0.04215 -0.0339 0.0373 1.0000
14.250 1.3817 0.05121 0.04489 -0.0336 0.0354 1.0000
14.500 1.3801 0.05424 0.04801 -0.0334 0.0338 1.0000
14.750 1.3820 0.05702 0.05096 -0.0334 0.0321 1.0000
15.000 1.3821 0.06010 0.05419 -0.0336 0.0304 1.0000
15.250 1.3798 0.06361 0.05781 -0.0341 0.0290 1.0000
15.500 1.3740 0.06770 0.06201 -0.0349 0.0279 1.0000
15.750 1.3706 0.07166 0.06613 -0.0359 0.0267 1.0000
16.000 1.3671 0.07578 0.07043 -0.0370 0.0255 1.0000
16.250 1.3619 0.08029 0.07509 -0.0386 0.0245 1.0000
16.500 1.3550 0.08521 0.08016 -0.0405 0.0236 1.0000
16.750 1.3462 0.09062 0.08569 -0.0428 0.0229 1.0000
17.000 1.3352 0.09654 0.09172 -0.0455 0.0222 1.0000
17.250 1.3273 0.10210 0.09746 -0.0480 0.0215 1.0000
17.500 1.3183 0.10797 0.10351 -0.0510 0.0208 1.0000
17.750 1.3087 0.11412 0.10982 -0.0542 0.0201 1.0000
18.000 1.2983 0.12052 0.11637 -0.0577 0.0195 1.0000
18.250 1.2877 0.12708 0.12307 -0.0614 0.0190 1.0000
18.500 1.2768 0.13381 0.12992 -0.0654 0.0185 1.0000
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Polar data table (+)
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