MH 45 9.85% (mh45-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 45 9.85% (mh45-il) Reynolds number: 50,000 Max Cl/Cd: 32.68 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh45-il-50000-n5.txt Download as CSV file: xf-mh45-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 45 9.85%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5602 0.09554 0.08916 0.0021 1.0000 0.0351
-9.000 -0.5622 0.09008 0.08378 -0.0014 1.0000 0.0349
-8.750 -0.5643 0.08456 0.07833 -0.0052 1.0000 0.0345
-8.500 -0.5684 0.07827 0.07208 -0.0103 1.0000 0.0339
-8.250 -0.5779 0.07205 0.06589 -0.0155 1.0000 0.0333
-8.000 -0.5853 0.06635 0.06009 -0.0193 1.0000 0.0328
-7.750 -0.5891 0.06102 0.05458 -0.0222 1.0000 0.0324
-7.500 -0.5892 0.05589 0.04917 -0.0242 1.0000 0.0325
-7.250 -0.5842 0.05125 0.04416 -0.0254 1.0000 0.0329
-7.000 -0.5749 0.04700 0.03946 -0.0260 1.0000 0.0337
-6.750 -0.5615 0.04315 0.03510 -0.0261 1.0000 0.0347
-6.500 -0.5448 0.03970 0.03105 -0.0259 1.0000 0.0360
-6.250 -0.5249 0.03673 0.02751 -0.0254 1.0000 0.0369
-6.000 -0.5045 0.03378 0.02439 -0.0250 1.0000 0.0381
-5.750 -0.4825 0.03152 0.02192 -0.0245 1.0000 0.0399
-5.500 -0.4602 0.02966 0.01981 -0.0238 1.0000 0.0439
-5.250 -0.4378 0.02791 0.01779 -0.0229 1.0000 0.0488
-5.000 -0.4187 0.02632 0.01619 -0.0218 1.0000 0.0538
-4.750 -0.4011 0.02496 0.01472 -0.0202 1.0000 0.0626
-4.500 -0.3862 0.02372 0.01345 -0.0184 1.0000 0.0749
-4.250 -0.3717 0.02247 0.01229 -0.0166 1.0000 0.0989
-4.000 -0.3558 0.02095 0.01128 -0.0154 1.0000 0.1681
-3.750 -0.3223 0.01989 0.01075 -0.0176 0.9858 0.3032
-3.500 -0.2876 0.01934 0.01050 -0.0194 0.9729 0.4048
-3.250 -0.2517 0.01887 0.01011 -0.0209 0.9608 0.4753
-3.000 -0.2169 0.01844 0.00978 -0.0221 0.9489 0.5414
-2.750 -0.1831 0.01807 0.00950 -0.0227 0.9372 0.6123
-2.500 -0.1489 0.01775 0.00933 -0.0230 0.9261 0.6912
-2.250 -0.1083 0.01753 0.00920 -0.0240 0.9161 0.7796
-2.000 -0.0526 0.01742 0.00898 -0.0280 0.9068 0.8678
-1.750 0.0127 0.01735 0.00863 -0.0344 0.8980 0.9348
-1.500 0.0741 0.01725 0.00821 -0.0407 0.8873 0.9856
-1.250 0.1082 0.01728 0.00798 -0.0423 0.8728 1.0000
-1.000 0.1293 0.01742 0.00792 -0.0413 0.8572 1.0000
-0.750 0.1500 0.01759 0.00789 -0.0401 0.8419 1.0000
-0.500 0.1708 0.01778 0.00790 -0.0389 0.8271 1.0000
-0.250 0.1918 0.01797 0.00794 -0.0375 0.8127 1.0000
0.000 0.2130 0.01817 0.00800 -0.0362 0.7986 1.0000
0.250 0.2344 0.01837 0.00807 -0.0348 0.7845 1.0000
0.500 0.2560 0.01856 0.00816 -0.0335 0.7707 1.0000
0.750 0.2778 0.01876 0.00825 -0.0321 0.7568 1.0000
1.000 0.2999 0.01894 0.00835 -0.0307 0.7430 1.0000
1.250 0.3221 0.01912 0.00847 -0.0294 0.7289 1.0000
1.500 0.3447 0.01931 0.00859 -0.0282 0.7145 1.0000
1.750 0.3674 0.01948 0.00872 -0.0269 0.7001 1.0000
2.000 0.3904 0.01965 0.00886 -0.0257 0.6855 1.0000
2.250 0.4135 0.01983 0.00902 -0.0245 0.6704 1.0000
2.500 0.4370 0.02001 0.00919 -0.0234 0.6547 1.0000
2.750 0.4606 0.02019 0.00937 -0.0223 0.6386 1.0000
3.000 0.4842 0.02037 0.00955 -0.0212 0.6223 1.0000
3.250 0.5080 0.02054 0.00976 -0.0201 0.6058 1.0000
3.500 0.5317 0.02071 0.00992 -0.0190 0.5891 1.0000
3.750 0.5556 0.02086 0.01007 -0.0178 0.5722 1.0000
4.000 0.5795 0.02104 0.01029 -0.0167 0.5547 1.0000
4.250 0.6034 0.02129 0.01058 -0.0157 0.5351 1.0000
4.500 0.6272 0.02150 0.01081 -0.0146 0.5162 1.0000
4.750 0.6511 0.02174 0.01105 -0.0135 0.4969 1.0000
5.000 0.6747 0.02206 0.01145 -0.0126 0.4756 1.0000
5.500 0.7214 0.02278 0.01221 -0.0106 0.4328 1.0000
5.750 0.7445 0.02318 0.01260 -0.0096 0.4112 1.0000
6.000 0.7672 0.02369 0.01320 -0.0088 0.3880 1.0000
6.250 0.7895 0.02423 0.01378 -0.0079 0.3652 1.0000
6.500 0.8114 0.02483 0.01438 -0.0069 0.3424 1.0000
6.750 0.8327 0.02553 0.01515 -0.0061 0.3188 1.0000
7.000 0.8536 0.02626 0.01587 -0.0052 0.2969 1.0000
7.250 0.8738 0.02711 0.01684 -0.0044 0.2742 1.0000
7.500 0.8935 0.02801 0.01774 -0.0035 0.2536 1.0000
7.750 0.9125 0.02903 0.01884 -0.0026 0.2332 1.0000
8.000 0.9309 0.03009 0.01992 -0.0017 0.2153 1.0000
8.250 0.9487 0.03125 0.02110 -0.0008 0.1984 1.0000
8.500 0.9660 0.03253 0.02253 0.0001 0.1827 1.0000
8.750 0.9827 0.03388 0.02397 0.0010 0.1685 1.0000
9.000 0.9981 0.03529 0.02546 0.0020 0.1552 1.0000
9.250 1.0138 0.03677 0.02696 0.0030 0.1441 1.0000
9.500 1.0272 0.03841 0.02881 0.0040 0.1328 1.0000
9.750 1.0391 0.04022 0.03083 0.0050 0.1225 1.0000
10.000 1.0516 0.04210 0.03281 0.0060 0.1142 1.0000
10.250 1.0609 0.04392 0.03476 0.0070 0.1059 1.0000
10.500 1.0667 0.04629 0.03745 0.0081 0.0987 1.0000
10.750 1.0745 0.04829 0.03951 0.0092 0.0927 1.0000
11.000 1.0732 0.05102 0.04251 0.0104 0.0878 1.0000
11.250 1.0694 0.05379 0.04550 0.0111 0.0831 1.0000
11.500 1.0767 0.05581 0.04741 0.0118 0.0785 1.0000
11.750 1.0642 0.06008 0.05209 0.0115 0.0764 1.0000
12.000 1.0497 0.06479 0.05711 0.0104 0.0745 1.0000
12.250 1.0332 0.07004 0.06261 0.0085 0.0730 1.0000
12.500 1.0124 0.07641 0.06918 0.0054 0.0723 1.0000
12.750 0.9834 0.08487 0.07783 0.0005 0.0728 1.0000
13.000 0.9446 0.09644 0.08953 -0.0068 0.0747 1.0000
13.250 0.9031 0.11032 0.10337 -0.0154 0.0760 1.0000
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Polar data table (+)
Polar graphs
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