MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 201 13.08% (mh201-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.93 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh201-il-1000000-n5.txt Download as CSV file: xf-mh201-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6475 0.06594 0.06399 -0.0617 0.9999 0.0034
-12.250 -0.6646 0.05399 0.05183 -0.0735 0.9988 0.0035
-12.000 -0.6921 0.04322 0.04074 -0.0848 0.9961 0.0034
-11.750 -0.7013 0.03749 0.03473 -0.0901 0.9933 0.0034
-11.500 -0.6993 0.03429 0.03136 -0.0923 0.9896 0.0034
-11.250 -0.6949 0.03098 0.02781 -0.0949 0.9857 0.0034
-11.000 -0.6924 0.02841 0.02502 -0.0953 0.9793 0.0034
-10.750 -0.6812 0.02600 0.02239 -0.0962 0.9731 0.0034
-10.500 -0.6726 0.02404 0.02020 -0.0952 0.9641 0.0034
-10.000 -0.6330 0.02087 0.01666 -0.0959 0.9519 0.0035
-9.750 -0.6029 0.01984 0.01550 -0.0977 0.9478 0.0036
-9.500 -0.5705 0.01857 0.01407 -0.1000 0.9438 0.0036
-9.250 -0.5382 0.01762 0.01299 -0.1020 0.9373 0.0036
-8.750 -0.4742 0.01585 0.01094 -0.1055 0.9218 0.0037
-8.500 -0.4458 0.01510 0.01007 -0.1064 0.9117 0.0037
-8.250 -0.4210 0.01426 0.00908 -0.1065 0.9001 0.0038
-8.000 -0.3978 0.01358 0.00827 -0.1061 0.8883 0.0038
-7.750 -0.3746 0.01299 0.00758 -0.1056 0.8782 0.0038
-7.500 -0.3519 0.01234 0.00681 -0.1051 0.8689 0.0039
-7.250 -0.3283 0.01184 0.00622 -0.1046 0.8598 0.0039
-7.000 -0.3039 0.01141 0.00571 -0.1043 0.8517 0.0040
-6.750 -0.2794 0.01098 0.00520 -0.1039 0.8438 0.0041
-6.500 -0.2540 0.01066 0.00481 -0.1036 0.8367 0.0041
-6.250 -0.2284 0.01033 0.00442 -0.1034 0.8292 0.0043
-6.000 -0.2024 0.01007 0.00411 -0.1032 0.8225 0.0044
-5.750 -0.1761 0.00982 0.00381 -0.1031 0.8155 0.0046
-5.250 -0.1227 0.00938 0.00327 -0.1029 0.8031 0.0053
-5.000 -0.0958 0.00918 0.00302 -0.1028 0.7969 0.0059
-4.750 -0.0688 0.00898 0.00279 -0.1027 0.7915 0.0076
-4.500 -0.0414 0.00879 0.00260 -0.1028 0.7859 0.0104
-4.250 -0.0142 0.00859 0.00242 -0.1028 0.7803 0.0179
-4.000 0.0132 0.00841 0.00225 -0.1028 0.7751 0.0278
-3.750 0.0407 0.00817 0.00208 -0.1030 0.7694 0.0489
-3.500 0.0676 0.00781 0.00190 -0.1031 0.7636 0.0986
-3.250 0.0946 0.00730 0.00172 -0.1035 0.7581 0.1861
-3.000 0.1224 0.00704 0.00160 -0.1037 0.7518 0.2362
-2.750 0.1501 0.00672 0.00148 -0.1041 0.7459 0.3061
-2.500 0.1785 0.00641 0.00138 -0.1045 0.7399 0.3739
-2.250 0.2067 0.00622 0.00130 -0.1048 0.7333 0.4239
-2.000 0.2353 0.00602 0.00123 -0.1051 0.7270 0.4751
-1.750 0.2638 0.00585 0.00118 -0.1055 0.7198 0.5255
-1.500 0.2922 0.00573 0.00115 -0.1057 0.7129 0.5713
-1.250 0.3207 0.00566 0.00115 -0.1059 0.7049 0.6062
-1.000 0.3489 0.00564 0.00116 -0.1060 0.6968 0.6315
-0.750 0.3770 0.00566 0.00118 -0.1060 0.6869 0.6493
-0.500 0.4051 0.00569 0.00120 -0.1061 0.6767 0.6629
-0.250 0.4329 0.00575 0.00122 -0.1061 0.6652 0.6740
0.000 0.4603 0.00582 0.00125 -0.1060 0.6515 0.6827
0.250 0.4875 0.00591 0.00128 -0.1058 0.6354 0.6905
0.500 0.5144 0.00601 0.00134 -0.1056 0.6168 0.6989
0.750 0.5406 0.00616 0.00139 -0.1053 0.5949 0.7061
1.000 0.5667 0.00632 0.00147 -0.1050 0.5731 0.7117
1.250 0.5927 0.00650 0.00155 -0.1046 0.5500 0.7163
1.500 0.6187 0.00669 0.00163 -0.1043 0.5267 0.7201
1.750 0.6441 0.00689 0.00174 -0.1039 0.5014 0.7234
2.000 0.6698 0.00709 0.00185 -0.1035 0.4772 0.7268
2.250 0.6951 0.00732 0.00198 -0.1031 0.4518 0.7304
2.500 0.7204 0.00756 0.00210 -0.1027 0.4258 0.7342
2.750 0.7455 0.00780 0.00224 -0.1023 0.4012 0.7378
3.250 0.7953 0.00829 0.00256 -0.1013 0.3527 0.7444
3.750 0.8450 0.00881 0.00288 -0.1004 0.3087 0.7496
4.250 0.8939 0.00934 0.00325 -0.0994 0.2682 0.7540
4.500 0.9186 0.00958 0.00344 -0.0989 0.2512 0.7563
4.750 0.9428 0.00985 0.00364 -0.0983 0.2330 0.7586
5.000 0.9670 0.01012 0.00385 -0.0978 0.2172 0.7609
5.250 0.9910 0.01039 0.00406 -0.0972 0.2016 0.7633
5.500 1.0148 0.01068 0.00429 -0.0966 0.1867 0.7656
5.750 1.0388 0.01095 0.00452 -0.0960 0.1747 0.7676
6.000 1.0620 0.01124 0.00476 -0.0953 0.1619 0.7699
6.250 1.0849 0.01155 0.00503 -0.0946 0.1489 0.7722
6.500 1.1074 0.01187 0.00531 -0.0938 0.1366 0.7746
6.750 1.1303 0.01216 0.00558 -0.0930 0.1267 0.7770
7.000 1.1530 0.01246 0.00586 -0.0922 0.1180 0.7794
7.250 1.1746 0.01280 0.00617 -0.0913 0.1082 0.7820
7.500 1.1962 0.01313 0.00648 -0.0903 0.0997 0.7843
7.750 1.2169 0.01346 0.00680 -0.0892 0.0920 0.7868
8.250 1.2555 0.01412 0.00746 -0.0863 0.0788 0.7922
8.500 1.2738 0.01452 0.00784 -0.0848 0.0727 0.7954
8.750 1.2931 0.01487 0.00820 -0.0835 0.0680 0.7984
9.000 1.3106 0.01530 0.00863 -0.0818 0.0622 0.8014
9.250 1.3290 0.01568 0.00904 -0.0804 0.0578 0.8046
9.500 1.3457 0.01617 0.00952 -0.0787 0.0522 0.8081
9.750 1.3634 0.01660 0.00997 -0.0772 0.0485 0.8117
10.000 1.3791 0.01714 0.01051 -0.0755 0.0434 0.8154
10.250 1.3954 0.01763 0.01103 -0.0738 0.0396 0.8198
10.500 1.4100 0.01824 0.01165 -0.0720 0.0351 0.8245
10.750 1.4248 0.01885 0.01227 -0.0703 0.0310 0.8291
11.000 1.4382 0.01952 0.01296 -0.0684 0.0273 0.8340
11.250 1.4527 0.02015 0.01363 -0.0667 0.0249 0.8397
11.750 1.4788 0.02160 0.01517 -0.0632 0.0202 0.8525
12.250 1.5019 0.02328 0.01695 -0.0595 0.0160 0.8709
12.500 1.5111 0.02426 0.01800 -0.0575 0.0139 0.8834
12.750 1.5210 0.02516 0.01899 -0.0556 0.0123 0.9006
13.000 1.5256 0.02606 0.02002 -0.0528 0.0110 0.9505
13.250 1.5363 0.02713 0.02116 -0.0514 0.0100 1.0000
13.500 1.5458 0.02834 0.02242 -0.0500 0.0090 1.0000
13.750 1.5545 0.02966 0.02378 -0.0486 0.0082 1.0000
14.000 1.5633 0.03099 0.02517 -0.0474 0.0074 1.0000
14.250 1.5708 0.03247 0.02671 -0.0461 0.0067 1.0000
14.500 1.5773 0.03407 0.02837 -0.0449 0.0062 1.0000
14.750 1.5842 0.03569 0.03006 -0.0438 0.0057 1.0000
15.000 1.5894 0.03750 0.03193 -0.0428 0.0051 1.0000
15.250 1.5937 0.03947 0.03398 -0.0418 0.0046 1.0000
15.500 1.5975 0.04156 0.03614 -0.0410 0.0042 1.0000
15.750 1.6012 0.04372 0.03839 -0.0404 0.0039 1.0000
16.000 1.6027 0.04619 0.04094 -0.0398 0.0034 1.0000
16.250 1.6028 0.04892 0.04375 -0.0394 0.0030 1.0000
16.500 1.6028 0.05177 0.04669 -0.0393 0.0026 1.0000
16.750 1.6016 0.05487 0.04988 -0.0393 0.0023 1.0000
17.000 1.5985 0.05835 0.05345 -0.0396 0.0020 1.0000
17.250 1.5954 0.06198 0.05719 -0.0401 0.0019 1.0000
17.500 1.5911 0.06592 0.06124 -0.0409 0.0017 1.0000
17.750 1.5846 0.07033 0.06576 -0.0421 0.0015 1.0000
18.000 1.5785 0.07486 0.07041 -0.0435 0.0014 1.0000
18.250 1.5674 0.08034 0.07601 -0.0454 0.0012 1.0000
18.500 1.5558 0.08610 0.08190 -0.0477 0.0011 1.0000
18.750 1.5450 0.09190 0.08783 -0.0502 0.0011 1.0000
19.000 1.5320 0.09826 0.09433 -0.0531 0.0010 1.0000
19.250 1.5173 0.10511 0.10131 -0.0565 0.0010 1.0000
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Polar data table (+)
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