MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 113 14.62% (mh113-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.23 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh113-il-1000000-n5.txt Download as CSV file: xf-mh113-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 113 14.62%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1988 0.04324 0.04017 -0.1705 0.8502 0.0099
-11.500 -0.2431 0.03478 0.03151 -0.1752 0.8346 0.0097
-11.250 -0.2800 0.02703 0.02351 -0.1816 0.8209 0.0097
-11.000 -0.2788 0.02369 0.01991 -0.1858 0.8118 0.0098
-10.750 -0.2676 0.02185 0.01789 -0.1868 0.8049 0.0098
-10.500 -0.2515 0.02049 0.01636 -0.1872 0.7985 0.0099
-10.250 -0.2326 0.01932 0.01502 -0.1875 0.7932 0.0100
-10.000 -0.2116 0.01830 0.01387 -0.1878 0.7876 0.0101
-9.750 -0.1892 0.01746 0.01289 -0.1880 0.7822 0.0102
-9.500 -0.1656 0.01675 0.01205 -0.1881 0.7774 0.0103
-9.250 -0.1408 0.01610 0.01130 -0.1883 0.7725 0.0104
-9.000 -0.1159 0.01545 0.01054 -0.1884 0.7674 0.0104
-8.750 -0.0907 0.01489 0.00986 -0.1884 0.7624 0.0105
-8.500 -0.0651 0.01420 0.00906 -0.1887 0.7580 0.0106
-8.250 -0.0391 0.01350 0.00827 -0.1889 0.7532 0.0108
-8.000 -0.0127 0.01301 0.00770 -0.1891 0.7481 0.0110
-7.750 0.0141 0.01261 0.00722 -0.1892 0.7435 0.0111
-7.500 0.0418 0.01223 0.00679 -0.1894 0.7391 0.0113
-7.250 0.0692 0.01189 0.00639 -0.1895 0.7340 0.0115
-7.000 0.0966 0.01159 0.00601 -0.1895 0.7291 0.0117
-6.750 0.1245 0.01129 0.00566 -0.1897 0.7247 0.0119
-6.500 0.1526 0.01100 0.00532 -0.1899 0.7198 0.0121
-6.250 0.1804 0.01073 0.00499 -0.1900 0.7147 0.0123
-6.000 0.2081 0.01050 0.00469 -0.1900 0.7098 0.0126
-5.750 0.2367 0.01026 0.00440 -0.1902 0.7051 0.0128
-5.500 0.2649 0.01005 0.00415 -0.1903 0.6996 0.0130
-5.250 0.2926 0.00989 0.00392 -0.1903 0.6944 0.0132
-5.000 0.3212 0.00963 0.00362 -0.1905 0.6895 0.0136
-4.750 0.3496 0.00944 0.00340 -0.1907 0.6839 0.0142
-4.500 0.3774 0.00931 0.00323 -0.1906 0.6782 0.0148
-4.250 0.4059 0.00918 0.00306 -0.1908 0.6730 0.0154
-4.000 0.4342 0.00906 0.00291 -0.1908 0.6670 0.0159
-3.750 0.4619 0.00897 0.00276 -0.1908 0.6607 0.0165
-3.500 0.4905 0.00884 0.00262 -0.1909 0.6552 0.0175
-3.250 0.5186 0.00876 0.00251 -0.1909 0.6486 0.0187
-3.000 0.5461 0.00870 0.00241 -0.1908 0.6423 0.0204
-2.750 0.5746 0.00861 0.00231 -0.1909 0.6359 0.0242
-2.500 0.6023 0.00853 0.00224 -0.1909 0.6289 0.0332
-2.250 0.6302 0.00845 0.00218 -0.1909 0.6225 0.0468
-2.000 0.6582 0.00838 0.00213 -0.1910 0.6154 0.0603
-1.750 0.6853 0.00835 0.00211 -0.1908 0.6083 0.0742
-1.500 0.7134 0.00830 0.00208 -0.1909 0.6011 0.0917
-1.250 0.7404 0.00827 0.00208 -0.1908 0.5934 0.1157
-1.000 0.7683 0.00820 0.00209 -0.1909 0.5862 0.1484
-0.750 0.7954 0.00817 0.00211 -0.1908 0.5781 0.1808
-0.500 0.8228 0.00815 0.00214 -0.1908 0.5707 0.2149
-0.250 0.8496 0.00817 0.00218 -0.1906 0.5623 0.2430
0.000 0.8765 0.00818 0.00223 -0.1904 0.5546 0.2717
0.250 0.9032 0.00820 0.00230 -0.1903 0.5458 0.3059
0.500 0.9296 0.00825 0.00236 -0.1900 0.5380 0.3362
0.750 0.9559 0.00829 0.00244 -0.1898 0.5292 0.3682
1.000 0.9821 0.00835 0.00253 -0.1895 0.5213 0.3989
1.250 1.0079 0.00843 0.00263 -0.1892 0.5124 0.4279
1.500 1.0335 0.00851 0.00273 -0.1888 0.5040 0.4567
1.750 1.0588 0.00860 0.00285 -0.1883 0.4951 0.4871
2.000 1.0840 0.00870 0.00297 -0.1879 0.4868 0.5158
2.250 1.1085 0.00882 0.00310 -0.1873 0.4774 0.5444
2.500 1.1334 0.00893 0.00323 -0.1867 0.4694 0.5725
2.750 1.1570 0.00907 0.00339 -0.1860 0.4600 0.6001
3.000 1.1808 0.00918 0.00353 -0.1853 0.4520 0.6293
3.250 1.2026 0.00933 0.00370 -0.1841 0.4429 0.6587
3.500 1.2253 0.00945 0.00385 -0.1832 0.4350 0.6898
3.750 1.2462 0.00962 0.00405 -0.1819 0.4258 0.7235
4.000 1.2683 0.00974 0.00424 -0.1808 0.4180 0.7631
4.250 1.2879 0.00991 0.00447 -0.1793 0.4089 0.8139
4.500 1.3011 0.00984 0.00465 -0.1762 0.4019 0.9422
4.750 1.3218 0.01008 0.00485 -0.1750 0.3928 1.0000
5.000 1.3433 0.01031 0.00505 -0.1739 0.3850 1.0000
5.500 1.3841 0.01087 0.00552 -0.1714 0.3680 1.0000
5.750 1.4030 0.01120 0.00580 -0.1699 0.3595 1.0000
6.000 1.4236 0.01147 0.00605 -0.1688 0.3523 1.0000
6.250 1.4420 0.01183 0.00636 -0.1672 0.3436 1.0000
6.500 1.4615 0.01214 0.00666 -0.1659 0.3363 1.0000
6.750 1.4791 0.01254 0.00702 -0.1644 0.3276 1.0000
7.000 1.4981 0.01289 0.00735 -0.1630 0.3206 1.0000
7.250 1.5154 0.01331 0.00774 -0.1614 0.3127 1.0000
7.500 1.5335 0.01372 0.00813 -0.1600 0.3060 1.0000
7.750 1.5503 0.01418 0.00856 -0.1584 0.2981 1.0000
8.000 1.5668 0.01466 0.00903 -0.1568 0.2905 1.0000
8.250 1.5831 0.01517 0.00952 -0.1552 0.2829 1.0000
8.500 1.5987 0.01572 0.01005 -0.1536 0.2758 1.0000
8.750 1.6151 0.01625 0.01057 -0.1521 0.2690 1.0000
9.000 1.6288 0.01693 0.01122 -0.1502 0.2609 1.0000
9.250 1.6445 0.01753 0.01181 -0.1487 0.2538 1.0000
9.500 1.6573 0.01829 0.01255 -0.1469 0.2462 1.0000
9.750 1.6724 0.01895 0.01321 -0.1454 0.2392 1.0000
10.000 1.6841 0.01982 0.01405 -0.1435 0.2313 1.0000
10.250 1.6982 0.02057 0.01480 -0.1420 0.2244 1.0000
10.500 1.7091 0.02154 0.01575 -0.1401 0.2167 1.0000
10.750 1.7220 0.02240 0.01662 -0.1386 0.2094 1.0000
11.000 1.7317 0.02350 0.01769 -0.1367 0.2014 1.0000
11.250 1.7440 0.02446 0.01865 -0.1353 0.1950 1.0000
11.500 1.7528 0.02568 0.01986 -0.1334 0.1870 1.0000
11.750 1.7640 0.02677 0.02096 -0.1320 0.1807 1.0000
12.000 1.7723 0.02810 0.02227 -0.1303 0.1735 1.0000
12.250 1.7821 0.02935 0.02353 -0.1288 0.1669 1.0000
12.500 1.7894 0.03083 0.02500 -0.1271 0.1599 1.0000
12.750 1.7988 0.03218 0.02636 -0.1258 0.1541 1.0000
13.000 1.8051 0.03383 0.02801 -0.1242 0.1473 1.0000
13.250 1.8137 0.03531 0.02951 -0.1229 0.1420 1.0000
13.500 1.8196 0.03708 0.03128 -0.1215 0.1357 1.0000
13.750 1.8257 0.03887 0.03308 -0.1202 0.1298 1.0000
14.000 1.8317 0.04072 0.03495 -0.1190 0.1240 1.0000
14.250 1.8359 0.04279 0.03703 -0.1178 0.1186 1.0000
14.500 1.8413 0.04478 0.03903 -0.1167 0.1128 1.0000
14.750 1.8433 0.04716 0.04142 -0.1156 0.1072 1.0000
15.000 1.8469 0.04946 0.04373 -0.1146 0.1013 1.0000
15.250 1.8482 0.05204 0.04632 -0.1137 0.0957 1.0000
15.500 1.8515 0.05447 0.04879 -0.1129 0.0912 1.0000
15.750 1.8511 0.05736 0.05169 -0.1121 0.0860 1.0000
16.000 1.8554 0.05977 0.05415 -0.1116 0.0829 1.0000
16.250 1.8569 0.06258 0.05700 -0.1111 0.0793 1.0000
16.500 1.8556 0.06578 0.06022 -0.1106 0.0752 1.0000
16.750 1.8576 0.06861 0.06311 -0.1103 0.0717 1.0000
17.000 1.8539 0.07223 0.06675 -0.1101 0.0672 1.0000
17.250 1.8536 0.07550 0.07007 -0.1100 0.0643 1.0000
17.500 1.8523 0.07893 0.07355 -0.1100 0.0609 1.0000
17.750 1.8486 0.08275 0.07741 -0.1101 0.0578 1.0000
18.000 1.8476 0.08625 0.08098 -0.1104 0.0556 1.0000
18.250 1.8450 0.09001 0.08480 -0.1107 0.0530 1.0000
18.500 1.8401 0.09416 0.08899 -0.1112 0.0503 1.0000
18.750 1.8375 0.09801 0.09292 -0.1118 0.0480 1.0000
19.000 1.8326 0.10225 0.09722 -0.1126 0.0455 1.0000
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Polar data table (+)
Polar graphs
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