MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: MH 112 Airfoil (mh112-il) Reynolds number: 200,000 Max Cl/Cd: 79.35 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh112-il-200000-n5.txt Download as CSV file: xf-mh112-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 112 Airfoil
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 0.2059 0.09378 0.08924 -0.1506 0.8766 0.0273
-10.000 0.2098 0.08529 0.08068 -0.1545 0.8617 0.0233
-9.750 0.2214 0.08317 0.07853 -0.1556 0.8554 0.0230
-9.500 0.2280 0.08075 0.07611 -0.1561 0.8481 0.0227
-9.250 0.2352 0.07792 0.07324 -0.1575 0.8419 0.0224
-9.000 0.2387 0.07497 0.07027 -0.1584 0.8355 0.0220
-8.750 0.2384 0.07169 0.06700 -0.1592 0.8283 0.0215
-8.500 0.2004 0.06130 0.05658 -0.1630 0.8210 0.0201
-8.250 0.1589 0.05263 0.04793 -0.1653 0.8121 0.0196
-8.000 0.0669 0.03518 0.02998 -0.1809 0.7998 0.0188
-7.750 0.0614 0.03099 0.02536 -0.1839 0.7921 0.0188
-7.500 0.0735 0.02812 0.02206 -0.1856 0.7867 0.0189
-7.250 0.0942 0.02585 0.01937 -0.1871 0.7827 0.0192
-7.000 0.1130 0.02428 0.01751 -0.1872 0.7774 0.0194
-6.750 0.1348 0.02297 0.01595 -0.1872 0.7721 0.0197
-6.500 0.1599 0.02184 0.01458 -0.1876 0.7677 0.0201
-6.250 0.1878 0.02100 0.01363 -0.1883 0.7640 0.0206
-6.000 0.2118 0.02033 0.01288 -0.1881 0.7591 0.0211
-5.750 0.2363 0.01967 0.01213 -0.1879 0.7540 0.0217
-5.500 0.2632 0.01901 0.01132 -0.1881 0.7495 0.0225
-5.250 0.2925 0.01836 0.01052 -0.1886 0.7457 0.0234
-5.000 0.3188 0.01792 0.01006 -0.1887 0.7411 0.0246
-4.750 0.3443 0.01754 0.00960 -0.1885 0.7359 0.0264
-4.500 0.3718 0.01713 0.00916 -0.1887 0.7312 0.0285
-4.250 0.4017 0.01670 0.00861 -0.1892 0.7272 0.0310
-4.000 0.4294 0.01635 0.00821 -0.1894 0.7228 0.0339
-3.750 0.4554 0.01605 0.00789 -0.1892 0.7175 0.0379
-3.500 0.4834 0.01574 0.00757 -0.1893 0.7126 0.0449
-3.250 0.5134 0.01544 0.00721 -0.1898 0.7085 0.0549
-3.000 0.5412 0.01521 0.00700 -0.1899 0.7040 0.0682
-2.750 0.5673 0.01503 0.00687 -0.1897 0.6986 0.0846
-2.500 0.5953 0.01483 0.00671 -0.1898 0.6937 0.1056
-2.250 0.6253 0.01464 0.00653 -0.1904 0.6895 0.1312
-2.000 0.6520 0.01451 0.00649 -0.1903 0.6845 0.1583
-1.750 0.6783 0.01441 0.00646 -0.1901 0.6791 0.1869
-1.500 0.7065 0.01431 0.00638 -0.1902 0.6742 0.2186
-1.250 0.7367 0.01420 0.00628 -0.1907 0.6700 0.2529
-1.000 0.7613 0.01417 0.00636 -0.1902 0.6643 0.2862
-0.750 0.7878 0.01414 0.00638 -0.1900 0.6589 0.3227
-0.500 0.8163 0.01408 0.00637 -0.1901 0.6541 0.3605
-0.250 0.8434 0.01408 0.00642 -0.1900 0.6491 0.3981
0.000 0.8681 0.01411 0.00653 -0.1894 0.6432 0.4345
0.250 0.8949 0.01413 0.00658 -0.1892 0.6379 0.4698
0.500 0.9234 0.01416 0.00659 -0.1892 0.6333 0.5042
0.750 0.9463 0.01424 0.00677 -0.1883 0.6270 0.5344
1.000 0.9715 0.01430 0.00685 -0.1877 0.6212 0.5645
1.250 0.9985 0.01434 0.00687 -0.1875 0.6159 0.5940
1.500 1.0204 0.01444 0.00705 -0.1863 0.6091 0.6224
1.750 1.0442 0.01451 0.00715 -0.1855 0.6026 0.6520
2.000 1.0693 0.01457 0.00720 -0.1848 0.5968 0.6838
2.250 1.0892 0.01467 0.00740 -0.1833 0.5898 0.7173
2.500 1.1108 0.01473 0.00751 -0.1819 0.5834 0.7571
2.750 1.1308 0.01476 0.00760 -0.1802 0.5778 0.8099
3.000 1.1431 0.01463 0.00765 -0.1769 0.5712 1.0000
3.250 1.1673 0.01484 0.00776 -0.1763 0.5650 1.0000
3.500 1.1906 0.01506 0.00790 -0.1756 0.5591 1.0000
3.750 1.2106 0.01530 0.00812 -0.1742 0.5524 1.0000
4.000 1.2331 0.01554 0.00827 -0.1734 0.5462 1.0000
4.250 1.2540 0.01581 0.00850 -0.1722 0.5401 1.0000
4.500 1.2732 0.01610 0.00877 -0.1708 0.5333 1.0000
4.750 1.2950 0.01637 0.00896 -0.1699 0.5270 1.0000
5.000 1.3134 0.01670 0.00928 -0.1684 0.5204 1.0000
5.250 1.3321 0.01703 0.00959 -0.1669 0.5135 1.0000
5.500 1.3525 0.01736 0.00985 -0.1658 0.5071 1.0000
5.750 1.3689 0.01776 0.01027 -0.1640 0.5001 1.0000
6.000 1.3869 0.01814 0.01061 -0.1626 0.4931 1.0000
6.250 1.4039 0.01857 0.01101 -0.1610 0.4860 1.0000
6.500 1.4197 0.01903 0.01147 -0.1592 0.4786 1.0000
6.750 1.4370 0.01949 0.01188 -0.1577 0.4717 1.0000
7.000 1.4508 0.02004 0.01246 -0.1558 0.4637 1.0000
7.250 1.4663 0.02058 0.01295 -0.1541 0.4563 1.0000
7.500 1.4801 0.02118 0.01358 -0.1523 0.4485 1.0000
7.750 1.4933 0.02183 0.01422 -0.1504 0.4403 1.0000
8.000 1.5067 0.02251 0.01490 -0.1486 0.4326 1.0000
8.250 1.5188 0.02327 0.01565 -0.1467 0.4240 1.0000
8.500 1.5310 0.02405 0.01643 -0.1449 0.4159 1.0000
8.750 1.5419 0.02492 0.01731 -0.1429 0.4071 1.0000
9.000 1.5531 0.02581 0.01819 -0.1411 0.3988 1.0000
9.250 1.5628 0.02680 0.01919 -0.1392 0.3899 1.0000
9.500 1.5731 0.02781 0.02020 -0.1374 0.3816 1.0000
9.750 1.5819 0.02894 0.02133 -0.1355 0.3726 1.0000
10.000 1.5912 0.03007 0.02246 -0.1337 0.3643 1.0000
10.250 1.5994 0.03131 0.02371 -0.1320 0.3557 1.0000
10.500 1.6079 0.03258 0.02498 -0.1303 0.3477 1.0000
10.750 1.6157 0.03394 0.02635 -0.1286 0.3394 1.0000
11.000 1.6234 0.03533 0.02775 -0.1270 0.3317 1.0000
11.250 1.6310 0.03679 0.02923 -0.1255 0.3238 1.0000
11.500 1.6381 0.03832 0.03075 -0.1240 0.3168 1.0000
11.750 1.6458 0.03987 0.03235 -0.1226 0.3092 1.0000
12.000 1.6518 0.04156 0.03401 -0.1212 0.3024 1.0000
12.250 1.6598 0.04316 0.03569 -0.1200 0.2954 1.0000
12.500 1.6658 0.04495 0.03749 -0.1188 0.2887 1.0000
12.750 1.6724 0.04674 0.03931 -0.1176 0.2824 1.0000
13.000 1.6789 0.04858 0.04121 -0.1166 0.2757 1.0000
13.250 1.6835 0.05061 0.04321 -0.1154 0.2696 1.0000
13.500 1.6905 0.05249 0.04520 -0.1145 0.2633 1.0000
13.750 1.6950 0.05464 0.04738 -0.1136 0.2570 1.0000
14.000 1.6998 0.05679 0.04955 -0.1127 0.2512 1.0000
14.250 1.7050 0.05897 0.05182 -0.1120 0.2449 1.0000
14.500 1.7079 0.06139 0.05425 -0.1112 0.2391 1.0000
14.750 1.7126 0.06369 0.05664 -0.1106 0.2333 1.0000
15.000 1.7158 0.06620 0.05921 -0.1100 0.2273 1.0000
15.250 1.7176 0.06886 0.06188 -0.1094 0.2218 1.0000
15.500 1.7214 0.07141 0.06454 -0.1091 0.2159 1.0000
15.750 1.7226 0.07426 0.06743 -0.1087 0.2102 1.0000
16.000 1.7243 0.07709 0.07033 -0.1084 0.2048 1.0000
16.250 1.7261 0.07997 0.07329 -0.1082 0.1989 1.0000
16.500 1.7252 0.08317 0.07651 -0.1081 0.1937 1.0000
16.750 1.7273 0.08609 0.07953 -0.1080 0.1883 1.0000
17.000 1.7268 0.08936 0.08287 -0.1081 0.1829 1.0000
17.250 1.7264 0.09261 0.08616 -0.1082 0.1781 1.0000
17.500 1.7267 0.09587 0.08952 -0.1085 0.1727 1.0000
17.750 1.7249 0.09936 0.09305 -0.1088 0.1678 1.0000
18.000 1.7246 0.10269 0.09646 -0.1092 0.1631 1.0000
18.250 1.7236 0.10618 0.10004 -0.1097 0.1581 1.0000
18.500 1.7213 0.10979 0.10368 -0.1103 0.1537 1.0000
18.750 1.7210 0.11320 0.10720 -0.1110 0.1492 1.0000
19.000 1.7194 0.11679 0.11086 -0.1118 0.1446 1.0000
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Polar data table (+)
Polar graphs
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