MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 114 13.02% (mh114-il) Reynolds number: 100,000 Max Cl/Cd: 60.75 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh114-il-100000-n5.txt Download as CSV file: xf-mh114-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 114 13.02%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.0345 0.10246 0.09743 -0.0935 0.9290 0.0463
-8.500 -0.0224 0.09909 0.09406 -0.0965 0.9244 0.0470
-8.250 -0.0175 0.09193 0.08688 -0.1033 0.9207 0.0300
-8.000 -0.0111 0.08980 0.08474 -0.1025 0.9127 0.0290
-7.750 0.0020 0.08623 0.08117 -0.1056 0.9084 0.0287
-7.500 0.0160 0.08181 0.07675 -0.1107 0.9051 0.0290
-7.250 0.0136 0.07973 0.07471 -0.1097 0.8949 0.0287
-7.000 0.0250 0.07564 0.07061 -0.1138 0.8905 0.0287
-6.750 0.0184 0.07348 0.06850 -0.1126 0.8799 0.0284
-6.500 0.0322 0.06906 0.06407 -0.1176 0.8751 0.0276
-6.250 0.0281 0.06592 0.06096 -0.1186 0.8647 0.0270
-6.000 0.0420 0.05255 0.04738 -0.1369 0.8582 0.0247
-5.750 0.0428 0.04826 0.04295 -0.1393 0.8475 0.0245
-5.500 0.0751 0.04042 0.03450 -0.1501 0.8437 0.0242
-5.250 0.1031 0.03509 0.02844 -0.1556 0.8381 0.0244
-5.000 0.1321 0.03146 0.02408 -0.1585 0.8323 0.0248
-4.750 0.1683 0.02930 0.02161 -0.1614 0.8293 0.0258
-4.500 0.2075 0.02753 0.01945 -0.1643 0.8271 0.0286
-4.250 0.2321 0.02644 0.01812 -0.1643 0.8210 0.0310
-4.000 0.2614 0.02529 0.01677 -0.1648 0.8159 0.0336
-3.750 0.2977 0.02406 0.01536 -0.1666 0.8128 0.0373
-3.500 0.3363 0.02300 0.01416 -0.1687 0.8104 0.0438
-3.250 0.3563 0.02264 0.01371 -0.1674 0.8028 0.0504
-3.000 0.3895 0.02188 0.01294 -0.1686 0.7984 0.0617
-2.750 0.4274 0.02111 0.01213 -0.1706 0.7954 0.0815
-2.500 0.4554 0.02067 0.01176 -0.1709 0.7898 0.1085
-2.250 0.4835 0.02028 0.01148 -0.1712 0.7837 0.1483
-2.000 0.5192 0.01973 0.01105 -0.1728 0.7800 0.2092
-1.750 0.5507 0.01938 0.01085 -0.1736 0.7754 0.2764
-1.500 0.5743 0.01931 0.01092 -0.1730 0.7681 0.3382
-1.250 0.6084 0.01897 0.01069 -0.1741 0.7639 0.4107
-1.000 0.6365 0.01885 0.01066 -0.1740 0.7583 0.4743
-0.750 0.6610 0.01883 0.01072 -0.1732 0.7513 0.5322
-0.500 0.6939 0.01857 0.01050 -0.1738 0.7471 0.5938
-0.250 0.7147 0.01863 0.01065 -0.1723 0.7397 0.6455
0.000 0.7400 0.01851 0.01058 -0.1713 0.7336 0.7004
0.250 0.7699 0.01819 0.01028 -0.1710 0.7295 0.7612
0.500 0.7787 0.01831 0.01053 -0.1670 0.7203 0.8230
0.750 0.8040 0.01787 0.01009 -0.1657 0.7150 1.0000
1.000 0.8284 0.01812 0.01023 -0.1653 0.7070 1.0000
1.250 0.8601 0.01816 0.01011 -0.1661 0.7007 1.0000
1.500 0.8890 0.01828 0.01011 -0.1663 0.6938 1.0000
1.750 0.9155 0.01844 0.01017 -0.1662 0.6861 1.0000
2.000 0.9479 0.01846 0.01006 -0.1669 0.6800 1.0000
2.250 0.9701 0.01873 0.01028 -0.1660 0.6711 1.0000
2.500 1.0037 0.01870 0.01013 -0.1670 0.6651 1.0000
2.750 1.0237 0.01903 0.01044 -0.1657 0.6555 1.0000
3.000 1.0558 0.01904 0.01035 -0.1664 0.6489 1.0000
3.250 1.0763 0.01936 0.01065 -0.1652 0.6392 1.0000
3.500 1.1053 0.01945 0.01067 -0.1654 0.6317 1.0000
3.750 1.1278 0.01972 0.01092 -0.1645 0.6223 1.0000
4.000 1.1535 0.01991 0.01108 -0.1641 0.6138 1.0000
4.250 1.1786 0.02011 0.01124 -0.1636 0.6048 1.0000
4.500 1.2008 0.02040 0.01152 -0.1627 0.5954 1.0000
4.750 1.2290 0.02053 0.01161 -0.1627 0.5870 1.0000
5.000 1.2477 0.02092 0.01202 -0.1612 0.5765 1.0000
5.250 1.2730 0.02114 0.01220 -0.1608 0.5675 1.0000
5.500 1.2942 0.02146 0.01252 -0.1597 0.5575 1.0000
5.750 1.3139 0.02182 0.01291 -0.1584 0.5474 1.0000
6.000 1.3395 0.02205 0.01308 -0.1580 0.5382 1.0000
6.250 1.3549 0.02251 0.01360 -0.1560 0.5273 1.0000
6.500 1.3747 0.02291 0.01401 -0.1548 0.5173 1.0000
6.750 1.3967 0.02325 0.01432 -0.1538 0.5075 1.0000
7.000 1.4114 0.02379 0.01492 -0.1518 0.4965 1.0000
7.250 1.4300 0.02425 0.01538 -0.1504 0.4864 1.0000
7.500 1.4487 0.02472 0.01585 -0.1490 0.4762 1.0000
7.750 1.4623 0.02535 0.01655 -0.1470 0.4653 1.0000
8.000 1.4791 0.02591 0.01711 -0.1454 0.4551 1.0000
8.250 1.4949 0.02650 0.01773 -0.1437 0.4447 1.0000
8.500 1.5071 0.02725 0.01855 -0.1416 0.4340 1.0000
8.750 1.5219 0.02793 0.01925 -0.1398 0.4239 1.0000
9.000 1.5351 0.02869 0.02004 -0.1379 0.4134 1.0000
9.250 1.5457 0.02958 0.02102 -0.1358 0.4028 1.0000
9.500 1.5585 0.03041 0.02187 -0.1339 0.3928 1.0000
9.750 1.5689 0.03137 0.02289 -0.1319 0.3824 1.0000
10.000 1.5781 0.03243 0.02404 -0.1298 0.3721 1.0000
10.250 1.5888 0.03344 0.02508 -0.1279 0.3622 1.0000
10.500 1.5966 0.03465 0.02637 -0.1258 0.3518 1.0000
10.750 1.6042 0.03592 0.02772 -0.1238 0.3417 1.0000
11.000 1.6127 0.03715 0.02897 -0.1219 0.3320 1.0000
11.250 1.6178 0.03866 0.03060 -0.1199 0.3215 1.0000
11.500 1.6236 0.04018 0.03221 -0.1180 0.3116 1.0000
11.750 1.6297 0.04169 0.03373 -0.1162 0.3020 1.0000
12.000 1.6325 0.04354 0.03573 -0.1143 0.2917 1.0000
12.250 1.6363 0.04536 0.03763 -0.1126 0.2821 1.0000
12.500 1.6394 0.04727 0.03958 -0.1110 0.2725 1.0000
12.750 1.6407 0.04946 0.04192 -0.1094 0.2625 1.0000
13.000 1.6426 0.05164 0.04416 -0.1079 0.2532 1.0000
13.250 1.6431 0.05402 0.04662 -0.1066 0.2437 1.0000
13.500 1.6431 0.05658 0.04930 -0.1054 0.2342 1.0000
13.750 1.6430 0.05917 0.05193 -0.1042 0.2254 1.0000
14.000 1.6414 0.06207 0.05496 -0.1033 0.2161 1.0000
14.250 1.6399 0.06504 0.05803 -0.1025 0.2074 1.0000
14.500 1.6376 0.06816 0.06121 -0.1018 0.1990 1.0000
14.750 1.6346 0.07153 0.06473 -0.1013 0.1903 1.0000
15.000 1.6315 0.07491 0.06814 -0.1009 0.1826 1.0000
15.250 1.6274 0.07861 0.07200 -0.1008 0.1744 1.0000
15.500 1.6235 0.08231 0.07577 -0.1007 0.1670 1.0000
15.750 1.6186 0.08627 0.07985 -0.1009 0.1595 1.0000
16.000 1.6139 0.09024 0.08392 -0.1012 0.1526 1.0000
16.250 1.6082 0.09448 0.08826 -0.1017 0.1456 1.0000
16.500 1.6031 0.09867 0.09256 -0.1023 0.1392 1.0000
16.750 1.5970 0.10312 0.09713 -0.1032 0.1327 1.0000
17.000 1.5917 0.10746 0.10156 -0.1042 0.1267 1.0000
17.250 1.5853 0.11210 0.10634 -0.1054 0.1207 1.0000
17.500 1.5803 0.11646 0.11073 -0.1067 0.1154 1.0000
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Polar data table (+)
Polar graphs
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