MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: MH 113 14.62% (mh113-il) Reynolds number: 500,000 Max Cl/Cd: 114.18 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh113-il-500000-n5.txt Download as CSV file: xf-mh113-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.1206 0.08605 0.08297 -0.1456 0.8924 0.0131
-10.500 0.1274 0.08167 0.07853 -0.1489 0.8822 0.0134
-10.250 0.1325 0.07814 0.07496 -0.1508 0.8714 0.0134
-9.750 -0.1026 0.03437 0.03064 -0.1727 0.8299 0.0126
-9.500 -0.1191 0.02744 0.02329 -0.1822 0.8183 0.0127
-9.250 -0.1109 0.02477 0.02028 -0.1841 0.8116 0.0128
-9.000 -0.0965 0.02280 0.01804 -0.1850 0.8052 0.0128
-8.750 -0.0777 0.02121 0.01618 -0.1856 0.7995 0.0130
-8.500 -0.0558 0.02002 0.01474 -0.1861 0.7946 0.0131
-8.250 -0.0329 0.01900 0.01353 -0.1863 0.7892 0.0132
-8.000 -0.0098 0.01787 0.01222 -0.1866 0.7839 0.0134
-7.750 0.0151 0.01701 0.01123 -0.1869 0.7792 0.0136
-7.500 0.0405 0.01633 0.01046 -0.1870 0.7745 0.0138
-7.250 0.0664 0.01573 0.00977 -0.1872 0.7694 0.0140
-7.000 0.0929 0.01518 0.00912 -0.1873 0.7645 0.0143
-6.750 0.1198 0.01468 0.00851 -0.1875 0.7601 0.0146
-6.500 0.1466 0.01418 0.00795 -0.1876 0.7552 0.0149
-6.250 0.1737 0.01373 0.00740 -0.1877 0.7500 0.0152
-6.000 0.2012 0.01333 0.00689 -0.1878 0.7454 0.0155
-5.750 0.2288 0.01297 0.00646 -0.1879 0.7407 0.0160
-5.500 0.2564 0.01259 0.00602 -0.1881 0.7356 0.0164
-5.250 0.2841 0.01224 0.00562 -0.1882 0.7305 0.0171
-5.000 0.3121 0.01196 0.00528 -0.1884 0.7258 0.0176
-4.750 0.3401 0.01169 0.00496 -0.1885 0.7207 0.0182
-4.500 0.3681 0.01145 0.00466 -0.1886 0.7153 0.0188
-4.000 0.4244 0.01100 0.00412 -0.1888 0.7051 0.0205
-3.750 0.4524 0.01083 0.00390 -0.1888 0.6995 0.0217
-3.500 0.4804 0.01069 0.00369 -0.1888 0.6941 0.0233
-3.250 0.5086 0.01053 0.00352 -0.1889 0.6887 0.0262
-3.000 0.5365 0.01037 0.00337 -0.1890 0.6827 0.0318
-2.750 0.5643 0.01024 0.00323 -0.1890 0.6771 0.0426
-2.500 0.5924 0.01010 0.00313 -0.1891 0.6712 0.0564
-2.250 0.6201 0.01001 0.00305 -0.1891 0.6648 0.0717
-2.000 0.6477 0.00992 0.00298 -0.1890 0.6589 0.0907
-1.750 0.6756 0.00981 0.00294 -0.1891 0.6524 0.1156
-1.500 0.7030 0.00971 0.00291 -0.1891 0.6457 0.1512
-1.250 0.7306 0.00962 0.00290 -0.1892 0.6394 0.1900
-1.000 0.7580 0.00956 0.00290 -0.1891 0.6324 0.2248
-0.750 0.7848 0.00954 0.00291 -0.1890 0.6256 0.2559
-0.500 0.8122 0.00950 0.00294 -0.1889 0.6184 0.2883
-0.250 0.8387 0.00951 0.00298 -0.1887 0.6110 0.3244
0.000 0.8657 0.00950 0.00303 -0.1886 0.6038 0.3612
0.250 0.8920 0.00952 0.00309 -0.1883 0.5960 0.3972
0.500 0.9182 0.00956 0.00316 -0.1880 0.5885 0.4320
0.750 0.9442 0.00960 0.00325 -0.1877 0.5803 0.4660
1.000 0.9698 0.00966 0.00334 -0.1873 0.5728 0.4988
1.250 0.9954 0.00973 0.00344 -0.1869 0.5642 0.5317
1.500 1.0203 0.00982 0.00356 -0.1863 0.5565 0.5640
1.750 1.0454 0.00990 0.00368 -0.1858 0.5478 0.5962
2.000 1.0695 0.01001 0.00382 -0.1851 0.5398 0.6273
2.250 1.0939 0.01010 0.00396 -0.1844 0.5311 0.6597
2.500 1.1170 0.01023 0.00411 -0.1836 0.5228 0.6930
2.750 1.1402 0.01033 0.00427 -0.1826 0.5139 0.7298
3.000 1.1617 0.01045 0.00445 -0.1814 0.5056 0.7719
3.250 1.1810 0.01052 0.00462 -0.1797 0.4970 0.8237
3.500 1.1920 0.01044 0.00469 -0.1760 0.4893 0.9959
3.750 1.2139 0.01065 0.00487 -0.1749 0.4805 1.0000
4.000 1.2345 0.01091 0.00506 -0.1736 0.4720 1.0000
4.250 1.2559 0.01115 0.00526 -0.1725 0.4633 1.0000
4.500 1.2761 0.01142 0.00548 -0.1712 0.4550 1.0000
4.750 1.2963 0.01170 0.00572 -0.1699 0.4458 1.0000
5.000 1.3162 0.01200 0.00597 -0.1685 0.4375 1.0000
5.250 1.3357 0.01231 0.00624 -0.1672 0.4287 1.0000
5.500 1.3549 0.01264 0.00653 -0.1658 0.4205 1.0000
5.750 1.3736 0.01299 0.00685 -0.1643 0.4115 1.0000
6.000 1.3922 0.01335 0.00718 -0.1628 0.4033 1.0000
6.250 1.4101 0.01374 0.00754 -0.1613 0.3948 1.0000
6.500 1.4281 0.01414 0.00792 -0.1598 0.3868 1.0000
6.750 1.4452 0.01458 0.00833 -0.1582 0.3783 1.0000
7.000 1.4626 0.01503 0.00876 -0.1567 0.3705 1.0000
7.250 1.4787 0.01553 0.00924 -0.1550 0.3618 1.0000
7.500 1.4954 0.01603 0.00972 -0.1535 0.3543 1.0000
7.750 1.5110 0.01658 0.01026 -0.1518 0.3459 1.0000
8.000 1.5268 0.01715 0.01081 -0.1502 0.3385 1.0000
8.250 1.5423 0.01775 0.01140 -0.1486 0.3305 1.0000
8.500 1.5568 0.01840 0.01205 -0.1469 0.3234 1.0000
8.750 1.5719 0.01905 0.01270 -0.1454 0.3154 1.0000
9.000 1.5852 0.01982 0.01345 -0.1436 0.3081 1.0000
9.250 1.6001 0.02051 0.01416 -0.1421 0.3006 1.0000
9.500 1.6119 0.02140 0.01503 -0.1403 0.2929 1.0000
9.750 1.6263 0.02217 0.01581 -0.1389 0.2855 1.0000
10.250 1.6509 0.02401 0.01766 -0.1356 0.2708 1.0000
10.500 1.6611 0.02511 0.01875 -0.1339 0.2632 1.0000
10.750 1.6736 0.02608 0.01974 -0.1324 0.2560 1.0000
11.000 1.6835 0.02726 0.02092 -0.1308 0.2486 1.0000
11.250 1.6946 0.02838 0.02206 -0.1293 0.2416 1.0000
11.500 1.7036 0.02969 0.02337 -0.1278 0.2339 1.0000
11.750 1.7135 0.03096 0.02466 -0.1263 0.2269 1.0000
12.000 1.7214 0.03243 0.02613 -0.1248 0.2190 1.0000
12.250 1.7306 0.03383 0.02755 -0.1234 0.2125 1.0000
12.500 1.7378 0.03543 0.02916 -0.1220 0.2047 1.0000
12.750 1.7452 0.03705 0.03080 -0.1207 0.1980 1.0000
13.000 1.7522 0.03875 0.03252 -0.1194 0.1908 1.0000
13.250 1.7578 0.04063 0.03442 -0.1181 0.1840 1.0000
13.500 1.7642 0.04247 0.03628 -0.1170 0.1770 1.0000
13.750 1.7683 0.04457 0.03840 -0.1158 0.1706 1.0000
14.000 1.7740 0.04657 0.04043 -0.1148 0.1640 1.0000
14.250 1.7769 0.04891 0.04279 -0.1137 0.1580 1.0000
14.500 1.7818 0.05109 0.04502 -0.1128 0.1516 1.0000
14.750 1.7830 0.05373 0.04767 -0.1119 0.1456 1.0000
15.000 1.7878 0.05600 0.05000 -0.1112 0.1403 1.0000
15.250 1.7888 0.05877 0.05279 -0.1105 0.1344 1.0000
15.500 1.7911 0.06145 0.05552 -0.1100 0.1295 1.0000
15.750 1.7927 0.06426 0.05838 -0.1095 0.1240 1.0000
16.000 1.7912 0.06751 0.06166 -0.1091 0.1191 1.0000
16.250 1.7935 0.07033 0.06454 -0.1088 0.1145 1.0000
16.500 1.7925 0.07363 0.06788 -0.1086 0.1097 1.0000
16.750 1.7910 0.07705 0.07137 -0.1085 0.1054 1.0000
17.000 1.7903 0.08044 0.07482 -0.1085 0.1007 1.0000
17.500 1.7847 0.08790 0.08239 -0.1089 0.0919 1.0000
17.750 1.7803 0.09195 0.08649 -0.1094 0.0875 1.0000
18.000 1.7766 0.09595 0.09055 -0.1099 0.0839 1.0000
18.250 1.7745 0.09974 0.09441 -0.1105 0.0802 1.0000
18.500 1.7686 0.10414 0.09886 -0.1113 0.0766 1.0000
18.750 1.7648 0.10824 0.10304 -0.1121 0.0734 1.0000
19.000 1.7612 0.11233 0.10720 -0.1131 0.0700 1.0000
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Polar data table (+)
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