MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 114 13.02% (mh114-il) Reynolds number: 200,000 Max Cl/Cd: 88.62 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh114-il-200000-n5.txt Download as CSV file: xf-mh114-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0506 0.11509 0.11125 -0.0931 0.9513 0.0244
-10.500 -0.0400 0.11146 0.10762 -0.0968 0.9479 0.0246
-10.250 -0.0329 0.10803 0.10421 -0.0995 0.9418 0.0247
-10.000 -0.0211 0.10417 0.10034 -0.1034 0.9383 0.0248
-9.750 -0.0061 0.10003 0.09619 -0.1077 0.9358 0.0248
-9.500 0.0042 0.09639 0.09256 -0.1104 0.9297 0.0248
-9.250 0.0200 0.09278 0.08893 -0.1138 0.9255 0.0248
-8.750 0.0582 0.08431 0.08041 -0.1199 0.9200 0.0160
-8.250 0.0781 0.07432 0.07038 -0.1288 0.9069 0.0137
-8.000 0.0899 0.07108 0.06713 -0.1317 0.8994 0.0134
-7.750 0.1029 0.06738 0.06341 -0.1355 0.8924 0.0132
-7.500 0.1073 0.06346 0.05949 -0.1383 0.8834 0.0131
-7.250 0.1118 0.05946 0.05547 -0.1415 0.8749 0.0130
-7.000 0.1069 0.05532 0.05134 -0.1439 0.8641 0.0129
-6.750 0.1077 0.04803 0.04401 -0.1527 0.8547 0.0126
-6.500 0.1010 0.02815 0.02299 -0.1748 0.8424 0.0119
-6.250 0.1216 0.02479 0.01908 -0.1768 0.8356 0.0123
-6.000 0.1485 0.02231 0.01609 -0.1786 0.8302 0.0127
-5.750 0.1803 0.02033 0.01355 -0.1804 0.8263 0.0139
-5.500 0.2051 0.01971 0.01288 -0.1805 0.8204 0.0148
-5.250 0.2330 0.01883 0.01179 -0.1809 0.8150 0.0161
-5.000 0.2642 0.01770 0.01037 -0.1818 0.8109 0.0171
-4.750 0.2911 0.01699 0.00959 -0.1820 0.8053 0.0180
-4.500 0.3188 0.01634 0.00883 -0.1822 0.7997 0.0195
-4.250 0.3497 0.01569 0.00806 -0.1830 0.7953 0.0215
-4.000 0.3778 0.01529 0.00757 -0.1832 0.7899 0.0253
-3.750 0.4056 0.01488 0.00710 -0.1834 0.7840 0.0294
-3.500 0.4364 0.01445 0.00661 -0.1841 0.7793 0.0361
-3.250 0.4649 0.01409 0.00623 -0.1844 0.7738 0.0460
-3.000 0.4928 0.01380 0.00593 -0.1845 0.7678 0.0606
-2.750 0.5235 0.01349 0.00562 -0.1852 0.7629 0.0833
-2.500 0.5513 0.01323 0.00546 -0.1853 0.7569 0.1150
-2.250 0.5794 0.01301 0.00532 -0.1855 0.7508 0.1551
-2.000 0.6101 0.01279 0.00515 -0.1862 0.7459 0.2008
-1.750 0.6365 0.01266 0.00512 -0.1861 0.7391 0.2482
-1.500 0.6651 0.01251 0.00506 -0.1863 0.7331 0.3014
-1.250 0.6940 0.01239 0.00502 -0.1866 0.7274 0.3553
-1.000 0.7205 0.01232 0.00505 -0.1864 0.7203 0.4060
-0.750 0.7495 0.01224 0.00501 -0.1866 0.7145 0.4563
-0.500 0.7756 0.01221 0.00507 -0.1863 0.7074 0.5032
-0.250 0.8028 0.01217 0.00509 -0.1861 0.7008 0.5489
0.000 0.8293 0.01216 0.00513 -0.1857 0.6942 0.5927
0.250 0.8547 0.01216 0.00520 -0.1851 0.6867 0.6348
0.500 0.8812 0.01216 0.00522 -0.1847 0.6803 0.6769
0.750 0.9047 0.01216 0.00531 -0.1837 0.6723 0.7187
1.250 0.9493 0.01214 0.00541 -0.1810 0.6573 0.8142
1.500 0.9677 0.01206 0.00536 -0.1787 0.6503 0.8863
1.750 0.9918 0.01204 0.00535 -0.1778 0.6416 1.0000
2.250 1.0448 0.01235 0.00550 -0.1775 0.6249 1.0000
2.500 1.0713 0.01252 0.00557 -0.1773 0.6166 1.0000
2.750 1.0963 0.01270 0.00570 -0.1768 0.6073 1.0000
3.000 1.1218 0.01289 0.00582 -0.1764 0.5985 1.0000
3.250 1.1466 0.01309 0.00596 -0.1759 0.5892 1.0000
3.500 1.1708 0.01330 0.00613 -0.1753 0.5797 1.0000
4.000 1.2184 0.01376 0.00649 -0.1740 0.5602 1.0000
4.250 1.2416 0.01401 0.00668 -0.1732 0.5506 1.0000
4.500 1.2643 0.01427 0.00691 -0.1723 0.5404 1.0000
4.750 1.2862 0.01454 0.00716 -0.1713 0.5301 1.0000
5.000 1.3079 0.01484 0.00740 -0.1703 0.5202 1.0000
5.250 1.3286 0.01514 0.00768 -0.1691 0.5095 1.0000
5.500 1.3485 0.01545 0.00798 -0.1677 0.4992 1.0000
5.750 1.3673 0.01579 0.00828 -0.1662 0.4890 1.0000
6.000 1.3856 0.01615 0.00862 -0.1646 0.4783 1.0000
6.250 1.4036 0.01653 0.00900 -0.1629 0.4678 1.0000
6.500 1.4208 0.01695 0.00938 -0.1612 0.4576 1.0000
6.750 1.4377 0.01737 0.00981 -0.1594 0.4467 1.0000
7.000 1.4543 0.01782 0.01026 -0.1576 0.4364 1.0000
7.250 1.4698 0.01833 0.01075 -0.1557 0.4261 1.0000
7.500 1.4854 0.01884 0.01127 -0.1539 0.4154 1.0000
7.750 1.5005 0.01939 0.01182 -0.1520 0.4052 1.0000
8.000 1.5143 0.02001 0.01243 -0.1499 0.3953 1.0000
8.250 1.5288 0.02061 0.01306 -0.1481 0.3847 1.0000
8.500 1.5423 0.02128 0.01374 -0.1461 0.3749 1.0000
8.750 1.5544 0.02203 0.01449 -0.1440 0.3648 1.0000
9.000 1.5678 0.02275 0.01526 -0.1421 0.3545 1.0000
9.250 1.5795 0.02358 0.01610 -0.1401 0.3448 1.0000
9.500 1.5906 0.02447 0.01701 -0.1381 0.3348 1.0000
9.750 1.6020 0.02537 0.01795 -0.1361 0.3245 1.0000
10.000 1.6118 0.02639 0.01900 -0.1341 0.3149 1.0000
10.250 1.6215 0.02746 0.02009 -0.1321 0.3047 1.0000
10.500 1.6315 0.02854 0.02123 -0.1303 0.2948 1.0000
10.750 1.6391 0.02981 0.02251 -0.1283 0.2852 1.0000
11.000 1.6477 0.03107 0.02381 -0.1264 0.2750 1.0000
11.250 1.6556 0.03241 0.02521 -0.1246 0.2652 1.0000
11.500 1.6611 0.03395 0.02677 -0.1227 0.2555 1.0000
11.750 1.6680 0.03546 0.02834 -0.1210 0.2453 1.0000
12.000 1.6740 0.03710 0.03002 -0.1194 0.2356 1.0000
12.250 1.6777 0.03896 0.03191 -0.1176 0.2262 1.0000
12.500 1.6830 0.04077 0.03378 -0.1161 0.2161 1.0000
12.750 1.6870 0.04275 0.03581 -0.1146 0.2066 1.0000
13.000 1.6885 0.04502 0.03810 -0.1132 0.1976 1.0000
13.250 1.6925 0.04714 0.04029 -0.1119 0.1880 1.0000
13.500 1.6946 0.04949 0.04270 -0.1107 0.1794 1.0000
13.750 1.6949 0.05212 0.04536 -0.1096 0.1708 1.0000
14.000 1.6973 0.05461 0.04794 -0.1086 0.1622 1.0000
14.250 1.6964 0.05752 0.05089 -0.1077 0.1544 1.0000
14.500 1.6969 0.06036 0.05380 -0.1070 0.1462 1.0000
14.750 1.6962 0.06342 0.05692 -0.1064 0.1389 1.0000
15.000 1.6943 0.06670 0.06027 -0.1059 0.1316 1.0000
15.250 1.6936 0.06992 0.06357 -0.1055 0.1247 1.0000
15.500 1.6900 0.07358 0.06729 -0.1053 0.1182 1.0000
15.750 1.6886 0.07702 0.07084 -0.1052 0.1117 1.0000
16.000 1.6837 0.08104 0.07491 -0.1053 0.1057 1.0000
16.250 1.6815 0.08474 0.07872 -0.1055 0.0998 1.0000
16.500 1.6759 0.08902 0.08306 -0.1059 0.0942 1.0000
16.750 1.6726 0.09300 0.08715 -0.1064 0.0890 1.0000
17.000 1.6670 0.09739 0.09162 -0.1071 0.0839 1.0000
17.250 1.6619 0.10178 0.09610 -0.1080 0.0794 1.0000
17.500 1.6575 0.10611 0.10054 -0.1089 0.0747 1.0000
17.750 1.6495 0.11107 0.10556 -0.1103 0.0709 1.0000
18.000 1.6468 0.11519 0.10981 -0.1114 0.0667 1.0000
18.250 1.6398 0.12005 0.11476 -0.1129 0.0629 1.0000
18.500 1.6344 0.12471 0.11952 -0.1145 0.0595 1.0000
18.750 1.6296 0.12927 0.12419 -0.1162 0.0558 1.0000
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Polar data table (+)
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