MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 114 13.02% (mh114-il) Reynolds number: 500,000 Max Cl/Cd: 120.96 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh114-il-500000-n5.txt Download as CSV file: xf-mh114-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.1268 0.14231 0.13973 -0.0805 0.9785 0.0108
-13.250 -0.1170 0.13822 0.13564 -0.0837 0.9763 0.0109
-12.750 -0.1001 0.13117 0.12860 -0.0879 0.9684 0.0110
-12.500 -0.0868 0.12828 0.12571 -0.0892 0.9650 0.0112
-12.000 -0.0655 0.12215 0.11958 -0.0929 0.9560 0.0114
-11.750 -0.0528 0.11884 0.11626 -0.0954 0.9524 0.0115
-11.500 -0.0387 0.11528 0.11270 -0.0985 0.9497 0.0116
-11.250 -0.0257 0.11181 0.10922 -0.1014 0.9450 0.0116
-11.000 -0.0103 0.10824 0.10563 -0.1049 0.9410 0.0118
-10.750 0.0070 0.10436 0.10173 -0.1091 0.9377 0.0119
-10.500 0.0264 0.10045 0.09781 -0.1139 0.9346 0.0120
-10.250 0.0453 0.09638 0.09371 -0.1189 0.9298 0.0120
-9.750 0.0807 0.08516 0.08240 -0.1314 0.9191 0.0082
-9.500 0.0998 0.08134 0.07854 -0.1363 0.9103 0.0080
-9.250 0.1186 0.07801 0.07515 -0.1407 0.9016 0.0078
-9.000 0.1312 0.07411 0.07119 -0.1445 0.8906 0.0076
-8.750 0.1374 0.07032 0.06735 -0.1471 0.8788 0.0074
-8.500 0.1407 0.06651 0.06350 -0.1492 0.8674 0.0071
-8.250 -0.0306 0.02641 0.02269 -0.1790 0.8309 0.0059
-8.000 -0.0179 0.02212 0.01783 -0.1826 0.8238 0.0059
-7.750 0.0024 0.01978 0.01510 -0.1839 0.8173 0.0060
-7.500 0.0262 0.01807 0.01304 -0.1848 0.8116 0.0061
-7.250 0.0514 0.01682 0.01153 -0.1854 0.8064 0.0062
-7.000 0.0771 0.01572 0.01022 -0.1859 0.8006 0.0063
-6.750 0.1038 0.01478 0.00909 -0.1864 0.7955 0.0065
-6.500 0.1309 0.01416 0.00835 -0.1867 0.7905 0.0068
-6.250 0.1581 0.01363 0.00771 -0.1869 0.7850 0.0070
-6.000 0.1858 0.01313 0.00708 -0.1872 0.7798 0.0073
-5.750 0.2137 0.01266 0.00649 -0.1874 0.7749 0.0078
-5.500 0.2415 0.01223 0.00596 -0.1876 0.7694 0.0082
-5.250 0.2696 0.01182 0.00545 -0.1878 0.7641 0.0086
-5.000 0.2978 0.01148 0.00504 -0.1881 0.7592 0.0092
-4.750 0.3259 0.01119 0.00469 -0.1882 0.7536 0.0100
-4.500 0.3541 0.01095 0.00436 -0.1884 0.7482 0.0111
-4.250 0.3823 0.01072 0.00408 -0.1885 0.7431 0.0128
-4.000 0.4105 0.01048 0.00381 -0.1887 0.7373 0.0152
-3.750 0.4387 0.01029 0.00356 -0.1888 0.7317 0.0181
-3.500 0.4670 0.01011 0.00335 -0.1889 0.7264 0.0224
-3.250 0.4951 0.00994 0.00318 -0.1890 0.7203 0.0301
-3.000 0.5232 0.00980 0.00302 -0.1892 0.7146 0.0401
-2.750 0.5514 0.00965 0.00290 -0.1893 0.7087 0.0530
-2.250 0.6075 0.00940 0.00269 -0.1895 0.6965 0.0959
-2.000 0.6356 0.00927 0.00263 -0.1897 0.6899 0.1266
-1.750 0.6633 0.00917 0.00258 -0.1897 0.6833 0.1605
-1.500 0.6913 0.00908 0.00255 -0.1899 0.6769 0.1950
-1.250 0.7190 0.00901 0.00253 -0.1899 0.6698 0.2315
-1.000 0.7466 0.00894 0.00253 -0.1900 0.6631 0.2755
-0.750 0.7742 0.00889 0.00254 -0.1900 0.6557 0.3174
-0.500 0.8014 0.00886 0.00257 -0.1900 0.6486 0.3597
-0.250 0.8288 0.00884 0.00261 -0.1899 0.6408 0.3995
0.000 0.8555 0.00886 0.00266 -0.1898 0.6331 0.4379
0.250 0.8827 0.00886 0.00272 -0.1897 0.6249 0.4774
0.500 0.9090 0.00890 0.00279 -0.1894 0.6169 0.5147
0.750 0.9356 0.00893 0.00287 -0.1892 0.6082 0.5515
1.000 0.9615 0.00899 0.00296 -0.1889 0.5996 0.5865
1.250 0.9875 0.00905 0.00306 -0.1885 0.5905 0.6207
1.500 1.0131 0.00912 0.00317 -0.1881 0.5818 0.6548
1.750 1.0380 0.00921 0.00329 -0.1875 0.5724 0.6897
2.000 1.0630 0.00928 0.00341 -0.1870 0.5632 0.7263
2.250 1.0865 0.00938 0.00356 -0.1861 0.5537 0.7659
2.500 1.1094 0.00944 0.00370 -0.1851 0.5439 0.8124
2.750 1.1277 0.00947 0.00382 -0.1830 0.5347 0.8762
3.000 1.1466 0.00948 0.00387 -0.1810 0.5250 1.0000
3.250 1.1709 0.00968 0.00401 -0.1805 0.5147 1.0000
3.500 1.1942 0.00991 0.00418 -0.1797 0.5047 1.0000
3.750 1.2176 0.01013 0.00435 -0.1789 0.4942 1.0000
4.000 1.2406 0.01035 0.00453 -0.1781 0.4840 1.0000
4.250 1.2617 0.01061 0.00472 -0.1769 0.4738 1.0000
4.500 1.2830 0.01085 0.00493 -0.1757 0.4629 1.0000
4.750 1.3038 0.01111 0.00515 -0.1745 0.4530 1.0000
5.000 1.3233 0.01142 0.00540 -0.1730 0.4424 1.0000
5.250 1.3441 0.01169 0.00565 -0.1718 0.4320 1.0000
5.500 1.3637 0.01200 0.00592 -0.1704 0.4218 1.0000
5.750 1.3821 0.01236 0.00623 -0.1688 0.4111 1.0000
6.000 1.4022 0.01267 0.00652 -0.1676 0.4010 1.0000
6.250 1.4206 0.01304 0.00686 -0.1661 0.3907 1.0000
6.750 1.4571 0.01382 0.00758 -0.1630 0.3702 1.0000
7.000 1.4744 0.01425 0.00800 -0.1614 0.3607 1.0000
7.250 1.4913 0.01471 0.00843 -0.1597 0.3504 1.0000
7.500 1.5087 0.01517 0.00887 -0.1581 0.3405 1.0000
7.750 1.5244 0.01570 0.00938 -0.1564 0.3310 1.0000
8.000 1.5405 0.01623 0.00990 -0.1547 0.3206 1.0000
8.250 1.5563 0.01678 0.01045 -0.1530 0.3112 1.0000
8.500 1.5704 0.01744 0.01108 -0.1511 0.3011 1.0000
8.750 1.5856 0.01806 0.01170 -0.1494 0.2910 1.0000
9.000 1.5999 0.01874 0.01238 -0.1477 0.2820 1.0000
9.500 1.6263 0.02028 0.01391 -0.1440 0.2616 1.0000
9.750 1.6386 0.02114 0.01476 -0.1422 0.2519 1.0000
10.250 1.6618 0.02302 0.01663 -0.1385 0.2316 1.0000
10.500 1.6726 0.02405 0.01766 -0.1367 0.2221 1.0000
10.750 1.6817 0.02523 0.01884 -0.1347 0.2120 1.0000
11.000 1.6917 0.02638 0.01999 -0.1330 0.2014 1.0000
11.250 1.7010 0.02762 0.02123 -0.1312 0.1920 1.0000
11.500 1.7084 0.02903 0.02263 -0.1294 0.1825 1.0000
11.750 1.7167 0.03042 0.02402 -0.1277 0.1729 1.0000
12.000 1.7242 0.03191 0.02553 -0.1260 0.1639 1.0000
12.250 1.7299 0.03359 0.02721 -0.1243 0.1550 1.0000
12.500 1.7365 0.03526 0.02889 -0.1228 0.1461 1.0000
12.750 1.7423 0.03704 0.03069 -0.1213 0.1379 1.0000
13.000 1.7463 0.03903 0.03268 -0.1197 0.1298 1.0000
13.250 1.7522 0.04090 0.03459 -0.1184 0.1224 1.0000
13.500 1.7553 0.04309 0.03680 -0.1171 0.1149 1.0000
13.750 1.7585 0.04535 0.03908 -0.1158 0.1070 1.0000
14.000 1.7618 0.04765 0.04141 -0.1147 0.1003 1.0000
14.250 1.7625 0.05030 0.04407 -0.1136 0.0932 1.0000
14.500 1.7656 0.05274 0.04656 -0.1128 0.0873 1.0000
15.000 1.7681 0.05827 0.05219 -0.1112 0.0763 1.0000
15.500 1.7675 0.06443 0.05843 -0.1101 0.0661 1.0000
15.750 1.7643 0.06800 0.06205 -0.1097 0.0612 1.0000
16.000 1.7638 0.07130 0.06542 -0.1095 0.0566 1.0000
16.250 1.7596 0.07518 0.06934 -0.1095 0.0523 1.0000
16.500 1.7580 0.07875 0.07298 -0.1095 0.0484 1.0000
16.750 1.7531 0.08288 0.07716 -0.1097 0.0447 1.0000
17.000 1.7505 0.08674 0.08112 -0.1101 0.0415 1.0000
17.250 1.7454 0.09104 0.08549 -0.1106 0.0383 1.0000
17.500 1.7410 0.09529 0.08981 -0.1112 0.0356 1.0000
17.750 1.7356 0.09974 0.09434 -0.1120 0.0328 1.0000
18.000 1.7291 0.10443 0.09911 -0.1130 0.0304 1.0000
18.250 1.7241 0.10895 0.10371 -0.1141 0.0279 1.0000
18.500 1.7167 0.11387 0.10871 -0.1155 0.0258 1.0000
18.750 1.7114 0.11849 0.11343 -0.1169 0.0236 1.0000
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Polar data table (+)
Polar graphs
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