MH 27 11.99% (mh27-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 27 11.99% (mh27-il) Reynolds number: 50,000 Max Cl/Cd: 33.59 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh27-il-50000.txt Download as CSV file: xf-mh27-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4974 0.10563 0.09927 -0.0124 1.0000 0.3281
-8.250 -0.5189 0.10378 0.09760 -0.0100 1.0000 0.3440
-6.250 -0.6933 0.06706 0.06057 -0.0066 1.0000 0.1680
-6.000 -0.6977 0.06020 0.05280 -0.0038 1.0000 0.1177
-5.750 -0.6954 0.05589 0.04793 0.0000 1.0000 0.1048
-5.500 -0.6879 0.05216 0.04389 0.0030 1.0000 0.0988
-5.250 -0.6833 0.04931 0.04003 0.0079 1.0000 0.0933
-5.000 -0.6689 0.04602 0.03653 0.0101 1.0000 0.0919
-4.750 -0.6551 0.04326 0.03326 0.0131 1.0000 0.0922
-4.500 -0.6371 0.04055 0.03015 0.0154 1.0000 0.0917
-4.250 -0.6158 0.03799 0.02716 0.0174 1.0000 0.0913
-4.000 -0.1915 0.03140 0.02280 -0.0386 1.0000 1.0000
-3.750 -0.1878 0.03066 0.02177 -0.0361 1.0000 1.0000
-3.500 -0.1822 0.03009 0.02093 -0.0336 1.0000 1.0000
-3.250 -0.1752 0.02963 0.02021 -0.0311 1.0000 1.0000
-3.000 -0.1671 0.02926 0.01959 -0.0286 1.0000 1.0000
-2.750 -0.1581 0.02897 0.01907 -0.0262 1.0000 1.0000
-2.500 -0.1485 0.02875 0.01863 -0.0238 1.0000 1.0000
-2.250 -0.1383 0.02858 0.01824 -0.0214 1.0000 1.0000
-2.000 -0.1278 0.02846 0.01790 -0.0190 1.0000 1.0000
-1.750 -0.1169 0.02838 0.01764 -0.0167 1.0000 1.0000
-1.500 -0.1058 0.02834 0.01744 -0.0144 1.0000 1.0000
-1.250 -0.0945 0.02834 0.01729 -0.0121 1.0000 1.0000
-1.000 -0.0831 0.02837 0.01719 -0.0098 1.0000 1.0000
-0.750 -0.0716 0.02844 0.01714 -0.0076 1.0000 1.0000
-0.500 -0.0600 0.02855 0.01710 -0.0054 1.0000 1.0000
-0.250 -0.0485 0.02869 0.01714 -0.0032 1.0000 1.0000
0.000 -0.0368 0.02886 0.01723 -0.0010 1.0000 1.0000
0.250 -0.0253 0.02907 0.01736 0.0011 1.0000 1.0000
0.500 -0.0139 0.02931 0.01753 0.0032 1.0000 1.0000
0.750 -0.0025 0.02959 0.01774 0.0053 1.0000 1.0000
1.000 0.0087 0.02991 0.01801 0.0073 1.0000 1.0000
1.250 0.0199 0.03027 0.01833 0.0093 1.0000 1.0000
1.500 0.0308 0.03067 0.01871 0.0113 1.0000 1.0000
1.750 0.0416 0.03111 0.01914 0.0131 1.0000 1.0000
2.000 0.0522 0.03161 0.01962 0.0150 1.0000 1.0000
2.250 0.0627 0.03215 0.02016 0.0167 1.0000 1.0000
2.500 0.0728 0.03275 0.02077 0.0184 1.0000 1.0000
2.750 0.0828 0.03340 0.02144 0.0200 1.0000 1.0000
3.000 0.0926 0.03411 0.02218 0.0216 1.0000 1.0000
3.250 0.1021 0.03489 0.02299 0.0230 1.0000 1.0000
3.500 0.1139 0.03579 0.02394 0.0238 0.9991 1.0000
3.750 0.1953 0.03823 0.02660 0.0106 0.9662 1.0000
4.000 0.2524 0.03964 0.02820 0.0031 0.9383 1.0000
4.250 0.3029 0.04062 0.02941 -0.0025 0.9120 1.0000
4.500 0.3511 0.04126 0.03026 -0.0072 0.8861 1.0000
4.750 0.3995 0.04160 0.03084 -0.0115 0.8606 1.0000
5.000 0.4491 0.04156 0.03111 -0.0154 0.8345 1.0000
5.250 0.5002 0.04109 0.03095 -0.0190 0.8076 1.0000
5.500 0.5536 0.04011 0.03031 -0.0220 0.7794 1.0000
5.750 0.6135 0.03835 0.02905 -0.0251 0.7496 1.0000
6.000 0.7051 0.03413 0.02548 -0.0304 0.7176 1.0000
6.250 0.8481 0.02757 0.01976 -0.0414 0.6380 1.0000
6.500 0.8983 0.02674 0.01857 -0.0415 0.5292 1.0000
6.750 0.9108 0.02766 0.01897 -0.0372 0.4455 1.0000
7.000 0.9172 0.02896 0.01978 -0.0325 0.3737 1.0000
7.250 0.9249 0.03055 0.02085 -0.0284 0.3089 1.0000
7.500 0.9354 0.03237 0.02235 -0.0250 0.2534 1.0000
7.750 0.9475 0.03435 0.02412 -0.0219 0.2082 1.0000
8.000 0.9691 0.03669 0.02612 -0.0207 0.1716 1.0000
8.250 0.9903 0.03923 0.02883 -0.0191 0.1479 1.0000
8.500 1.0108 0.04193 0.03153 -0.0179 0.1303 1.0000
8.750 1.0300 0.04488 0.03461 -0.0163 0.1178 1.0000
9.000 1.0328 0.04779 0.03819 -0.0115 0.1134 1.0000
9.250 1.0394 0.05076 0.04150 -0.0079 0.1086 1.0000
9.500 1.0433 0.05394 0.04485 -0.0044 0.1032 1.0000
9.750 1.0299 0.05645 0.04783 0.0020 0.1007 1.0000
10.000 1.0180 0.05912 0.05085 0.0077 0.0987 1.0000
10.250 1.0037 0.06201 0.05403 0.0134 0.0978 1.0000
10.500 0.9849 0.06505 0.05734 0.0193 0.0980 1.0000
10.750 0.9627 0.06772 0.06021 0.0253 0.0988 1.0000
11.000 0.9362 0.07044 0.06310 0.0312 0.0993 1.0000
11.250 0.9115 0.07347 0.06629 0.0359 0.1005 1.0000
11.500 0.8849 0.07703 0.06997 0.0397 0.1014 1.0000
11.750 0.8602 0.08093 0.07396 0.0422 0.1023 1.0000
12.000 0.8384 0.08532 0.07843 0.0436 0.1033 1.0000
12.250 0.8217 0.09036 0.08350 0.0442 0.1043 1.0000
12.500 0.5754 0.11020 0.10347 0.0298 0.1566 1.0000
12.750 0.5687 0.11550 0.10875 0.0289 0.1578 1.0000
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Polar data table (+)
Polar graphs
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