MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 114 13.02% (mh114-il) Reynolds number: 200,000 Max Cl/Cd: 89.71 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh114-il-200000.txt Download as CSV file: xf-mh114-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.0165 0.09932 0.09578 -0.0986 0.9441 0.0401
-8.500 -0.0095 0.09560 0.09208 -0.1060 0.9387 0.0420
-8.250 0.0039 0.09078 0.08727 -0.1147 0.9359 0.0424
-8.000 0.0192 0.08791 0.08440 -0.1117 0.9310 0.0432
-7.750 0.0372 0.08508 0.08156 -0.1129 0.9267 0.0442
-7.500 0.0581 0.08161 0.07809 -0.1168 0.9240 0.0462
-7.250 0.0783 0.07722 0.07369 -0.1245 0.9215 0.0491
-7.000 0.0671 0.07308 0.06959 -0.1339 0.9076 0.0503
-6.750 0.0906 0.06961 0.06612 -0.1321 0.9070 0.0515
-6.500 0.1193 0.06659 0.06307 -0.1352 0.9055 0.0533
-6.250 0.1168 0.06486 0.06136 -0.1341 0.8944 0.0547
-6.000 0.1763 0.04094 0.03756 -0.1397 0.8746 0.0621
-5.750 0.1435 0.05262 0.04897 -0.1558 0.8777 0.0610
-5.500 0.1715 0.05064 0.04700 -0.1566 0.8756 0.0628
-5.250 0.1813 0.04816 0.04447 -0.1577 0.8672 0.0654
-5.000 0.2249 0.02685 0.02081 -0.1783 0.8606 0.0298
-4.750 0.2629 0.02521 0.01922 -0.1813 0.8587 0.0330
-4.500 0.2832 0.02370 0.01730 -0.1804 0.8510 0.0342
-4.250 0.3186 0.02172 0.01487 -0.1820 0.8471 0.0347
-4.000 0.3573 0.01986 0.01276 -0.1840 0.8444 0.0367
-3.750 0.3966 0.01882 0.01157 -0.1860 0.8421 0.0415
-3.500 0.4146 0.01835 0.01116 -0.1844 0.8338 0.0469
-3.250 0.4496 0.01742 0.01018 -0.1857 0.8298 0.0576
-3.000 0.4879 0.01647 0.00926 -0.1877 0.8268 0.0773
-2.750 0.5125 0.01606 0.00894 -0.1872 0.8200 0.1040
-2.500 0.5448 0.01546 0.00848 -0.1882 0.8148 0.1575
-2.250 0.5816 0.01484 0.00809 -0.1901 0.8112 0.2385
-2.000 0.6076 0.01466 0.00809 -0.1900 0.8046 0.3083
-1.750 0.6374 0.01441 0.00798 -0.1903 0.7988 0.3807
-1.500 0.6723 0.01409 0.00777 -0.1915 0.7948 0.4554
-1.250 0.6958 0.01407 0.00790 -0.1907 0.7875 0.5143
-1.000 0.7252 0.01392 0.00782 -0.1907 0.7817 0.5739
-0.750 0.7589 0.01369 0.00763 -0.1914 0.7776 0.6305
-0.500 0.7782 0.01376 0.00782 -0.1896 0.7692 0.6774
-0.250 0.8068 0.01358 0.00769 -0.1892 0.7639 0.7284
0.000 0.8289 0.01353 0.00772 -0.1877 0.7573 0.7780
0.250 0.8479 0.01339 0.00767 -0.1854 0.7503 0.8327
0.500 0.8689 0.01307 0.00734 -0.1831 0.7455 0.9137
0.750 0.8943 0.01310 0.00736 -0.1827 0.7367 1.0000
1.000 0.9292 0.01308 0.00716 -0.1841 0.7310 1.0000
1.250 0.9551 0.01323 0.00725 -0.1839 0.7228 1.0000
1.500 0.9864 0.01325 0.00714 -0.1845 0.7162 1.0000
1.750 1.0134 0.01337 0.00719 -0.1844 0.7084 1.0000
2.000 1.0425 0.01343 0.00715 -0.1846 0.7009 1.0000
2.250 1.0698 0.01354 0.00720 -0.1845 0.6931 1.0000
2.500 1.0976 0.01362 0.00721 -0.1845 0.6850 1.0000
2.750 1.1242 0.01374 0.00728 -0.1842 0.6769 1.0000
3.000 1.1518 0.01383 0.00730 -0.1841 0.6686 1.0000
3.250 1.1770 0.01398 0.00742 -0.1836 0.6596 1.0000
3.500 1.2053 0.01407 0.00743 -0.1837 0.6514 1.0000
3.750 1.2285 0.01425 0.00761 -0.1828 0.6416 1.0000
4.000 1.2577 0.01436 0.00761 -0.1831 0.6334 1.0000
4.250 1.2793 0.01456 0.00783 -0.1819 0.6228 1.0000
4.500 1.3043 0.01474 0.00799 -0.1814 0.6133 1.0000
4.750 1.3300 0.01491 0.00809 -0.1810 0.6037 1.0000
5.000 1.3515 0.01515 0.00834 -0.1798 0.5928 1.0000
5.250 1.3762 0.01537 0.00852 -0.1793 0.5829 1.0000
5.500 1.3994 0.01560 0.00872 -0.1785 0.5723 1.0000
5.750 1.4199 0.01588 0.00902 -0.1772 0.5611 1.0000
6.000 1.4427 0.01616 0.00926 -0.1763 0.5505 1.0000
6.250 1.4651 0.01645 0.00950 -0.1754 0.5396 1.0000
6.500 1.4832 0.01678 0.00987 -0.1736 0.5280 1.0000
6.750 1.5034 0.01712 0.01020 -0.1724 0.5169 1.0000
7.000 1.5251 0.01748 0.01049 -0.1713 0.5062 1.0000
7.250 1.5408 0.01786 0.01091 -0.1692 0.4944 1.0000
7.500 1.5573 0.01827 0.01133 -0.1673 0.4832 1.0000
7.750 1.5747 0.01869 0.01172 -0.1656 0.4724 1.0000
8.000 1.5889 0.01913 0.01217 -0.1632 0.4613 1.0000
8.250 1.6015 0.01962 0.01270 -0.1607 0.4502 1.0000
8.500 1.6165 0.02014 0.01321 -0.1587 0.4395 1.0000
8.750 1.6300 0.02069 0.01374 -0.1564 0.4287 1.0000
9.000 1.6405 0.02129 0.01441 -0.1537 0.4176 1.0000
9.250 1.6531 0.02193 0.01505 -0.1514 0.4071 1.0000
9.500 1.6652 0.02261 0.01571 -0.1491 0.3965 1.0000
9.750 1.6737 0.02336 0.01655 -0.1463 0.3855 1.0000
10.000 1.6838 0.02416 0.01737 -0.1439 0.3749 1.0000
10.250 1.6943 0.02501 0.01818 -0.1416 0.3646 1.0000
10.500 1.7008 0.02596 0.01923 -0.1389 0.3535 1.0000
10.750 1.7089 0.02696 0.02028 -0.1364 0.3431 1.0000
11.000 1.7170 0.02803 0.02131 -0.1341 0.3327 1.0000
11.250 1.7220 0.02922 0.02261 -0.1315 0.3218 1.0000
11.500 1.7278 0.03048 0.02392 -0.1292 0.3112 1.0000
11.750 1.7333 0.03183 0.02525 -0.1269 0.3010 1.0000
12.000 1.7369 0.03331 0.02682 -0.1246 0.2901 1.0000
12.250 1.7407 0.03487 0.02845 -0.1224 0.2793 1.0000
12.500 1.7437 0.03657 0.03015 -0.1203 0.2691 1.0000
12.750 1.7456 0.03839 0.03201 -0.1182 0.2586 1.0000
13.000 1.7476 0.04031 0.03402 -0.1163 0.2480 1.0000
13.250 1.7488 0.04239 0.03612 -0.1145 0.2380 1.0000
13.500 1.7487 0.04464 0.03840 -0.1127 0.2280 1.0000
13.750 1.7492 0.04696 0.04082 -0.1112 0.2175 1.0000
14.000 1.7487 0.04946 0.04336 -0.1097 0.2079 1.0000
14.250 1.7466 0.05220 0.04608 -0.1084 0.1986 1.0000
14.500 1.7460 0.05492 0.04893 -0.1073 0.1888 1.0000
14.750 1.7439 0.05788 0.05192 -0.1062 0.1799 1.0000
15.000 1.7404 0.06107 0.05513 -0.1053 0.1713 1.0000
15.250 1.7383 0.06425 0.05844 -0.1047 0.1624 1.0000
15.500 1.7338 0.06776 0.06194 -0.1040 0.1546 1.0000
15.750 1.7301 0.07130 0.06559 -0.1037 0.1463 1.0000
16.000 1.7257 0.07501 0.06936 -0.1034 0.1388 1.0000
16.250 1.7201 0.07897 0.07336 -0.1034 0.1316 1.0000
16.500 1.7159 0.08287 0.07737 -0.1035 0.1245 1.0000
16.750 1.7091 0.08713 0.08164 -0.1038 0.1181 1.0000
17.000 1.7046 0.09122 0.08587 -0.1042 0.1116 1.0000
17.250 1.6974 0.09569 0.09034 -0.1048 0.1058 1.0000
17.500 1.6925 0.09997 0.09476 -0.1055 0.0998 1.0000
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Polar data table (+)
Polar graphs
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