MH 27 11.99% (mh27-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 27 11.99% (mh27-il) Reynolds number: 200,000 Max Cl/Cd: 54.72 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh27-il-200000-n5.txt Download as CSV file: xf-mh27-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 27 11.99%
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5060 0.08873 0.08527 -0.0481 0.9929 0.0075
-9.750 -0.5142 0.08208 0.07864 -0.0529 0.9910 0.0074
-9.500 -0.5295 0.07390 0.07044 -0.0596 0.9885 0.0073
-9.250 -0.5430 0.06923 0.06568 -0.0615 0.9864 0.0072
-9.000 -0.5591 0.06440 0.06071 -0.0618 0.9839 0.0071
-8.750 -0.5795 0.06163 0.05782 -0.0578 0.9803 0.0071
-8.500 -0.5967 0.05842 0.05446 -0.0538 0.9759 0.0070
-8.250 -0.6052 0.05418 0.04998 -0.0512 0.9728 0.0069
-8.000 -0.6097 0.05065 0.04622 -0.0482 0.9696 0.0067
-7.750 -0.6180 0.04761 0.04294 -0.0434 0.9651 0.0066
-7.500 -0.6209 0.04354 0.03849 -0.0394 0.9616 0.0066
-7.250 -0.6133 0.04033 0.03488 -0.0370 0.9593 0.0064
-7.000 -0.6097 0.03710 0.03123 -0.0330 0.9562 0.0063
-6.750 -0.6070 0.03460 0.02835 -0.0285 0.9520 0.0063
-6.500 -0.5947 0.03193 0.02523 -0.0256 0.9493 0.0063
-6.250 -0.5760 0.02961 0.02249 -0.0239 0.9474 0.0063
-6.000 -0.5525 0.02760 0.02009 -0.0231 0.9460 0.0064
-5.750 -0.5263 0.02585 0.01801 -0.0227 0.9450 0.0067
-5.500 -0.5113 0.02479 0.01677 -0.0201 0.9417 0.0067
-5.250 -0.4928 0.02362 0.01541 -0.0181 0.9385 0.0072
-5.000 -0.4700 0.02274 0.01439 -0.0172 0.9362 0.0075
-4.750 -0.4463 0.02175 0.01334 -0.0167 0.9341 0.0092
-4.500 -0.4196 0.02108 0.01256 -0.0167 0.9325 0.0105
-4.250 -0.3902 0.02058 0.01195 -0.0172 0.9312 0.0123
-4.000 -0.3830 0.01993 0.01122 -0.0130 0.9251 0.0140
-3.750 -0.3598 0.01934 0.01053 -0.0121 0.9222 0.0183
-3.500 -0.3341 0.01867 0.00992 -0.0118 0.9200 0.0358
-3.250 -0.3093 0.01776 0.00949 -0.0116 0.9183 0.1230
-3.000 -0.3024 0.01703 0.00919 -0.0077 0.9121 0.2211
-2.750 -0.2866 0.01615 0.00888 -0.0057 0.9082 0.3609
-2.250 -0.1667 0.01551 0.01020 -0.0184 0.9124 0.8605
-2.000 -0.1352 0.01582 0.01037 -0.0188 0.9094 0.8836
-1.750 -0.1065 0.01607 0.01052 -0.0186 0.9067 0.9028
-1.500 -0.0575 0.01664 0.01097 -0.0225 0.9061 0.9176
-1.250 -0.0067 0.01701 0.01123 -0.0271 0.9055 0.9263
-1.000 0.0277 0.01711 0.01124 -0.0286 0.9023 0.9325
-0.750 0.0611 0.01719 0.01126 -0.0298 0.8975 0.9380
-0.500 0.0949 0.01718 0.01118 -0.0312 0.8943 0.9443
-0.250 0.1432 0.01712 0.01107 -0.0356 0.8928 0.9469
0.000 0.1893 0.01700 0.01092 -0.0396 0.8914 0.9500
0.250 0.2059 0.01703 0.01094 -0.0373 0.8826 0.9575
0.500 0.2503 0.01678 0.01067 -0.0410 0.8799 0.9590
0.750 0.2945 0.01648 0.01036 -0.0445 0.8778 0.9604
1.000 0.3179 0.01637 0.01027 -0.0437 0.8680 0.9647
1.250 0.3565 0.01602 0.00994 -0.0460 0.8647 0.9668
1.500 0.3760 0.01589 0.00983 -0.0444 0.8538 0.9712
1.750 0.4058 0.01564 0.00962 -0.0449 0.8440 0.9735
2.000 0.4373 0.01532 0.00933 -0.0457 0.8353 0.9756
2.500 0.4972 0.01470 0.00880 -0.0466 0.8112 0.9802
2.750 0.5289 0.01434 0.00848 -0.0472 0.7946 0.9821
3.000 0.5767 0.01376 0.00793 -0.0511 0.7744 0.9815
3.250 0.6538 0.01307 0.00715 -0.0613 0.7333 0.9764
3.500 0.7005 0.01299 0.00682 -0.0651 0.6740 0.9753
3.750 0.7262 0.01327 0.00685 -0.0647 0.6141 0.9772
4.000 0.7432 0.01366 0.00700 -0.0626 0.5593 0.9802
4.250 0.7571 0.01410 0.00721 -0.0599 0.5076 0.9834
4.500 0.7763 0.01449 0.00739 -0.0586 0.4541 0.9856
4.750 0.7937 0.01493 0.00763 -0.0569 0.4036 0.9882
5.000 0.8106 0.01539 0.00790 -0.0551 0.3572 0.9908
5.250 0.8268 0.01590 0.00826 -0.0532 0.3117 0.9933
5.500 0.8453 0.01637 0.00857 -0.0519 0.2697 0.9952
5.750 0.8649 0.01690 0.00892 -0.0509 0.2245 0.9973
6.000 0.8841 0.01744 0.00931 -0.0498 0.1868 0.9991
6.250 0.8980 0.01796 0.00971 -0.0475 0.1551 1.0000
6.500 0.9053 0.01845 0.01012 -0.0438 0.1302 1.0000
6.750 0.9124 0.01897 0.01054 -0.0401 0.1064 1.0000
7.000 0.9199 0.01948 0.01098 -0.0365 0.0867 1.0000
7.250 0.9275 0.02000 0.01151 -0.0329 0.0707 1.0000
7.500 0.9355 0.02052 0.01203 -0.0293 0.0591 1.0000
7.750 0.9430 0.02108 0.01261 -0.0257 0.0492 1.0000
8.000 0.9496 0.02173 0.01324 -0.0220 0.0415 1.0000
8.250 0.9573 0.02229 0.01389 -0.0185 0.0356 1.0000
8.500 0.9623 0.02304 0.01464 -0.0146 0.0307 1.0000
8.750 0.9693 0.02366 0.01539 -0.0110 0.0279 1.0000
9.000 0.9752 0.02437 0.01620 -0.0073 0.0251 1.0000
9.250 0.9784 0.02526 0.01713 -0.0034 0.0224 1.0000
9.500 0.9833 0.02606 0.01805 0.0003 0.0204 1.0000
9.750 0.9892 0.02685 0.01896 0.0038 0.0183 1.0000
10.000 0.9957 0.02758 0.01982 0.0071 0.0163 1.0000
10.250 0.9960 0.02876 0.02105 0.0111 0.0143 1.0000
10.500 0.9992 0.02984 0.02228 0.0147 0.0130 1.0000
10.750 1.0062 0.03060 0.02316 0.0176 0.0112 1.0000
11.000 1.0085 0.03174 0.02441 0.0211 0.0101 1.0000
11.250 1.0114 0.03279 0.02555 0.0242 0.0092 1.0000
11.500 1.0086 0.03444 0.02732 0.0280 0.0081 1.0000
11.750 1.0090 0.03593 0.02899 0.0313 0.0078 1.0000
12.000 1.0082 0.03759 0.03084 0.0345 0.0071 1.0000
12.250 1.0059 0.03943 0.03286 0.0376 0.0066 1.0000
12.500 1.0029 0.04132 0.03491 0.0405 0.0062 1.0000
12.750 0.9991 0.04341 0.03717 0.0432 0.0060 1.0000
13.000 0.9943 0.04553 0.03944 0.0455 0.0057 1.0000
13.250 0.9885 0.04798 0.04207 0.0476 0.0057 1.0000
13.500 0.9803 0.05071 0.04496 0.0493 0.0055 1.0000
13.750 0.9714 0.05377 0.04821 0.0507 0.0055 1.0000
14.000 0.9600 0.05727 0.05187 0.0514 0.0053 1.0000
14.250 0.9465 0.06135 0.05614 0.0516 0.0052 1.0000
14.500 0.9323 0.06586 0.06082 0.0511 0.0051 1.0000
14.750 0.9203 0.07048 0.06565 0.0501 0.0052 1.0000
15.000 0.9031 0.07626 0.07162 0.0482 0.0052 1.0000
15.250 0.8831 0.08298 0.07850 0.0452 0.0051 1.0000
15.500 0.8678 0.08945 0.08516 0.0422 0.0052 1.0000
15.750 0.8501 0.09677 0.09263 0.0384 0.0052 1.0000
16.000 0.8288 0.10537 0.10140 0.0339 0.0053 1.0000
16.250 0.7938 0.11827 0.11456 0.0274 0.0057 1.0000
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