MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 113 14.62% (mh113-il) Reynolds number: 50,000 Max Cl/Cd: 20.31 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh113-il-50000-n5.txt Download as CSV file: xf-mh113-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.0876 0.12015 0.11346 -0.0754 0.9225 0.1167
-8.250 -0.0796 0.11739 0.11070 -0.0780 0.9173 0.1184
-8.000 -0.0770 0.11506 0.10840 -0.0797 0.9112 0.1196
-7.750 -0.0702 0.11213 0.10549 -0.0798 0.9044 0.1168
-7.500 -0.0723 0.10502 0.09829 -0.0855 0.8991 0.0696
-7.250 -0.0767 0.10303 0.09635 -0.0840 0.8905 0.0673
-7.000 -0.0885 0.09896 0.09230 -0.0871 0.8832 0.0622
-6.750 -0.0911 0.09731 0.09068 -0.0853 0.8751 0.0614
-6.500 -0.0908 0.09475 0.08815 -0.0856 0.8682 0.0607
-6.250 -0.0879 0.09161 0.08503 -0.0874 0.8620 0.0603
-6.000 -0.0950 0.08926 0.08274 -0.0870 0.8526 0.0600
-5.750 -0.0831 0.08482 0.07827 -0.0919 0.8478 0.0596
-5.500 -0.0941 0.08253 0.07603 -0.0913 0.8374 0.0593
-5.250 -0.0798 0.07717 0.07059 -0.0978 0.8321 0.0592
-5.000 -0.0777 0.07298 0.06635 -0.1011 0.8237 0.0586
-4.750 -0.0595 0.06673 0.05987 -0.1087 0.8176 0.0583
-4.500 -0.0223 0.05913 0.05176 -0.1198 0.8142 0.0577
-4.250 -0.0001 0.05474 0.04691 -0.1246 0.8070 0.0578
-4.000 0.0356 0.05065 0.04222 -0.1301 0.8021 0.0587
-3.750 0.0804 0.04695 0.03773 -0.1358 0.7988 0.0616
-3.500 0.1217 0.04497 0.03546 -0.1392 0.7961 0.0656
-3.250 0.1361 0.04433 0.03458 -0.1383 0.7872 0.0680
-3.000 0.1733 0.04260 0.03230 -0.1404 0.7830 0.0720
-2.750 0.2113 0.04148 0.03109 -0.1424 0.7798 0.0793
-2.500 0.2274 0.04127 0.03076 -0.1412 0.7715 0.0848
-2.250 0.2579 0.04057 0.02991 -0.1419 0.7663 0.0958
-2.000 0.2959 0.03968 0.02899 -0.1436 0.7630 0.1139
-1.750 0.3123 0.03982 0.02912 -0.1426 0.7544 0.1319
-1.500 0.3449 0.03934 0.02865 -0.1437 0.7492 0.1666
-1.250 0.3851 0.03860 0.02802 -0.1458 0.7459 0.2205
-1.000 0.4001 0.03907 0.02860 -0.1447 0.7366 0.2633
-0.750 0.4328 0.03879 0.02851 -0.1456 0.7316 0.3314
-0.500 0.4707 0.03829 0.02818 -0.1468 0.7284 0.4133
-0.250 0.4796 0.03915 0.02920 -0.1446 0.7178 0.4639
0.000 0.5105 0.03889 0.02908 -0.1445 0.7134 0.5421
0.250 0.5420 0.03841 0.02873 -0.1440 0.7101 0.6221
0.500 0.5444 0.03942 0.02988 -0.1405 0.6987 0.6763
0.750 0.5674 0.03879 0.02940 -0.1381 0.6949 0.7702
1.000 0.5614 0.03935 0.03017 -0.1330 0.6833 0.9589
1.250 0.6008 0.03934 0.02979 -0.1349 0.6790 1.0000
1.750 0.6485 0.04067 0.03067 -0.1350 0.6637 1.0000
2.000 0.6871 0.04043 0.03018 -0.1362 0.6605 1.0000
2.250 0.6938 0.04204 0.03169 -0.1346 0.6484 1.0000
2.500 0.7299 0.04186 0.03130 -0.1354 0.6447 1.0000
3.000 0.7713 0.04335 0.03255 -0.1343 0.6289 1.0000
3.250 0.8097 0.04285 0.03189 -0.1351 0.6262 1.0000
3.500 0.8112 0.04494 0.03396 -0.1331 0.6131 1.0000
3.750 0.8485 0.04442 0.03330 -0.1337 0.6101 1.0000
4.000 0.8503 0.04658 0.03544 -0.1318 0.5974 1.0000
4.250 0.8859 0.04611 0.03488 -0.1321 0.5940 1.0000
4.750 0.9221 0.04791 0.03658 -0.1305 0.5779 1.0000
5.250 0.9571 0.04981 0.03843 -0.1288 0.5617 1.0000
5.500 0.9951 0.04899 0.03755 -0.1291 0.5592 1.0000
5.750 0.9902 0.05191 0.04050 -0.1271 0.5456 1.0000
6.000 1.0276 0.05105 0.03961 -0.1273 0.5428 1.0000
6.250 1.0218 0.05417 0.04276 -0.1254 0.5294 1.0000
6.500 1.0580 0.05335 0.04191 -0.1254 0.5264 1.0000
7.000 1.0867 0.05583 0.04444 -0.1234 0.5100 1.0000
7.500 1.1136 0.05854 0.04721 -0.1215 0.4936 1.0000
8.000 1.1377 0.06161 0.05037 -0.1197 0.4771 1.0000
8.500 1.1598 0.06495 0.05380 -0.1179 0.4606 1.0000
8.750 1.1963 0.06373 0.05259 -0.1175 0.4579 1.0000
9.250 1.2126 0.06769 0.05670 -0.1156 0.4408 1.0000
9.750 1.2275 0.07193 0.06108 -0.1139 0.4239 1.0000
10.250 1.2399 0.07660 0.06591 -0.1124 0.4072 1.0000
10.750 1.2515 0.08147 0.07094 -0.1111 0.3906 1.0000
11.250 1.2614 0.08666 0.07632 -0.1101 0.3742 1.0000
11.750 1.2687 0.09236 0.08220 -0.1094 0.3580 1.0000
12.250 1.2784 0.09776 0.08779 -0.1089 0.3424 1.0000
12.750 1.2791 0.10472 0.09495 -0.1090 0.3257 1.0000
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Polar data table (+)
Polar graphs
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