MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 113 14.62% (mh113-il) Reynolds number: 200,000 Max Cl/Cd: 83.63 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh113-il-200000-n5.txt Download as CSV file: xf-mh113-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.0516 0.10641 0.10238 -0.1147 0.9275 0.0333
-10.500 0.0571 0.10227 0.09822 -0.1204 0.9215 0.0357
-10.250 0.0695 0.09778 0.09371 -0.1260 0.9173 0.0358
-9.750 0.0978 0.08828 0.08415 -0.1320 0.9070 0.0270
-9.250 0.1203 0.07850 0.07428 -0.1403 0.8951 0.0229
-9.000 0.1336 0.07597 0.07173 -0.1423 0.8875 0.0227
-8.750 0.1474 0.07246 0.06817 -0.1458 0.8814 0.0224
-8.500 0.1498 0.06920 0.06491 -0.1472 0.8720 0.0223
-8.250 0.1557 0.06532 0.06098 -0.1501 0.8649 0.0221
-8.000 0.1510 0.06166 0.05735 -0.1511 0.8552 0.0219
-7.750 0.1448 0.05676 0.05240 -0.1538 0.8472 0.0217
-7.500 0.0387 0.03065 0.02530 -0.1772 0.8268 0.0202
-7.250 0.0534 0.02811 0.02241 -0.1785 0.8201 0.0204
-7.000 0.0766 0.02616 0.02013 -0.1800 0.8153 0.0209
-6.750 0.1005 0.02453 0.01818 -0.1811 0.8106 0.0216
-6.500 0.1225 0.02296 0.01625 -0.1813 0.8046 0.0224
-6.250 0.1490 0.02153 0.01442 -0.1820 0.7998 0.0229
-6.000 0.1781 0.02045 0.01320 -0.1829 0.7961 0.0234
-5.750 0.2016 0.01971 0.01237 -0.1826 0.7903 0.0238
-5.500 0.2279 0.01897 0.01152 -0.1826 0.7850 0.0244
-5.250 0.2569 0.01823 0.01064 -0.1831 0.7808 0.0252
-5.000 0.2845 0.01760 0.00988 -0.1833 0.7760 0.0260
-4.750 0.3103 0.01706 0.00924 -0.1831 0.7704 0.0269
-4.500 0.3386 0.01657 0.00871 -0.1834 0.7655 0.0280
-4.000 0.3945 0.01581 0.00784 -0.1838 0.7555 0.0324
-3.750 0.4224 0.01546 0.00742 -0.1839 0.7501 0.0349
-3.500 0.4529 0.01508 0.00696 -0.1845 0.7457 0.0385
-3.250 0.4801 0.01478 0.00665 -0.1845 0.7400 0.0441
-3.000 0.5076 0.01450 0.00638 -0.1845 0.7343 0.0554
-2.750 0.5375 0.01421 0.00610 -0.1850 0.7294 0.0738
-2.500 0.5653 0.01401 0.00594 -0.1851 0.7239 0.0961
-2.250 0.5922 0.01381 0.00585 -0.1851 0.7177 0.1283
-2.000 0.6216 0.01360 0.00571 -0.1855 0.7125 0.1701
-1.750 0.6493 0.01347 0.00565 -0.1856 0.7068 0.2075
-1.500 0.6761 0.01336 0.00562 -0.1855 0.7004 0.2444
-1.250 0.7053 0.01324 0.00554 -0.1858 0.6950 0.2843
-1.000 0.7319 0.01317 0.00556 -0.1856 0.6886 0.3255
-0.750 0.7590 0.01311 0.00557 -0.1855 0.6820 0.3689
-0.250 0.8129 0.01305 0.00563 -0.1851 0.6693 0.4543
0.000 0.8401 0.01303 0.00566 -0.1849 0.6628 0.4954
0.250 0.8665 0.01303 0.00572 -0.1846 0.6563 0.5353
0.500 0.8917 0.01305 0.00580 -0.1840 0.6491 0.5738
0.750 0.9185 0.01306 0.00582 -0.1837 0.6428 0.6125
1.000 0.9420 0.01311 0.00596 -0.1827 0.6350 0.6497
1.250 0.9671 0.01314 0.00601 -0.1821 0.6280 0.6885
1.500 0.9898 0.01318 0.00612 -0.1809 0.6206 0.7286
1.750 1.0118 0.01320 0.00620 -0.1796 0.6131 0.7736
2.000 1.0312 0.01320 0.00626 -0.1776 0.6058 0.8295
2.250 1.0481 0.01305 0.00622 -0.1750 0.5980 1.0000
2.500 1.0743 0.01324 0.00629 -0.1748 0.5905 1.0000
2.750 1.0987 0.01343 0.00643 -0.1742 0.5819 1.0000
3.000 1.1240 0.01363 0.00653 -0.1738 0.5743 1.0000
3.250 1.1474 0.01385 0.00670 -0.1731 0.5655 1.0000
3.500 1.1717 0.01407 0.00683 -0.1725 0.5577 1.0000
3.750 1.1941 0.01431 0.00703 -0.1716 0.5488 1.0000
4.000 1.2171 0.01456 0.00720 -0.1708 0.5406 1.0000
4.250 1.2385 0.01481 0.00743 -0.1697 0.5317 1.0000
4.500 1.2597 0.01508 0.00763 -0.1685 0.5235 1.0000
4.750 1.2792 0.01536 0.00789 -0.1671 0.5144 1.0000
5.000 1.2991 0.01567 0.00814 -0.1658 0.5062 1.0000
5.250 1.3180 0.01599 0.00843 -0.1643 0.4972 1.0000
5.500 1.3370 0.01634 0.00873 -0.1628 0.4888 1.0000
5.750 1.3552 0.01670 0.00908 -0.1612 0.4799 1.0000
6.000 1.3734 0.01708 0.00942 -0.1597 0.4715 1.0000
6.250 1.3905 0.01749 0.00981 -0.1580 0.4625 1.0000
6.500 1.4079 0.01792 0.01022 -0.1564 0.4542 1.0000
6.750 1.4241 0.01838 0.01067 -0.1547 0.4453 1.0000
7.000 1.4405 0.01887 0.01114 -0.1530 0.4369 1.0000
7.250 1.4559 0.01939 0.01164 -0.1512 0.4282 1.0000
7.500 1.4714 0.01993 0.01218 -0.1495 0.4199 1.0000
7.750 1.4860 0.02053 0.01277 -0.1476 0.4114 1.0000
8.000 1.5007 0.02113 0.01338 -0.1459 0.4032 1.0000
8.250 1.5143 0.02180 0.01404 -0.1441 0.3948 1.0000
8.500 1.5283 0.02249 0.01475 -0.1423 0.3869 1.0000
8.750 1.5410 0.02324 0.01550 -0.1404 0.3784 1.0000
9.000 1.5540 0.02401 0.01628 -0.1387 0.3706 1.0000
9.250 1.5660 0.02485 0.01713 -0.1369 0.3623 1.0000
9.500 1.5782 0.02571 0.01802 -0.1351 0.3547 1.0000
9.750 1.5897 0.02664 0.01897 -0.1334 0.3466 1.0000
10.000 1.6006 0.02762 0.01996 -0.1316 0.3391 1.0000
10.250 1.6116 0.02863 0.02101 -0.1299 0.3311 1.0000
10.500 1.6214 0.02974 0.02214 -0.1282 0.3238 1.0000
10.750 1.6315 0.03087 0.02332 -0.1266 0.3157 1.0000
11.000 1.6401 0.03212 0.02456 -0.1248 0.3087 1.0000
11.250 1.6497 0.03334 0.02586 -0.1233 0.3007 1.0000
11.500 1.6568 0.03477 0.02729 -0.1216 0.2936 1.0000
11.750 1.6661 0.03609 0.02869 -0.1202 0.2858 1.0000
12.000 1.6718 0.03771 0.03031 -0.1186 0.2785 1.0000
12.250 1.6805 0.03917 0.03185 -0.1173 0.2710 1.0000
12.500 1.6856 0.04094 0.03364 -0.1158 0.2637 1.0000
12.750 1.6927 0.04260 0.03538 -0.1146 0.2563 1.0000
13.000 1.6973 0.04452 0.03733 -0.1132 0.2490 1.0000
13.250 1.7029 0.04641 0.03928 -0.1121 0.2419 1.0000
13.500 1.7067 0.04852 0.04143 -0.1109 0.2344 1.0000
13.750 1.7111 0.05063 0.04361 -0.1099 0.2275 1.0000
14.000 1.7140 0.05294 0.04597 -0.1089 0.2201 1.0000
14.250 1.7169 0.05531 0.04839 -0.1080 0.2135 1.0000
14.500 1.7196 0.05777 0.05092 -0.1072 0.2063 1.0000
14.750 1.7203 0.06050 0.05369 -0.1064 0.1999 1.0000
15.000 1.7229 0.06308 0.05636 -0.1058 0.1929 1.0000
15.250 1.7214 0.06618 0.05948 -0.1052 0.1867 1.0000
15.500 1.7237 0.06893 0.06234 -0.1049 0.1800 1.0000
15.750 1.7215 0.07225 0.06570 -0.1045 0.1739 1.0000
16.000 1.7225 0.07526 0.06880 -0.1043 0.1678 1.0000
16.250 1.7204 0.07871 0.07231 -0.1042 0.1617 1.0000
16.500 1.7187 0.08216 0.07583 -0.1042 0.1563 1.0000
16.750 1.7175 0.08561 0.07937 -0.1044 0.1505 1.0000
17.250 1.7126 0.09298 0.08690 -0.1050 0.1401 1.0000
17.500 1.7086 0.09695 0.09094 -0.1055 0.1350 1.0000
17.750 1.7052 0.10086 0.09492 -0.1061 0.1304 1.0000
18.000 1.7031 0.10464 0.09880 -0.1068 0.1254 1.0000
18.250 1.6977 0.10894 0.10316 -0.1078 0.1210 1.0000
18.500 1.6954 0.11278 0.10711 -0.1087 0.1167 1.0000
18.750 1.6924 0.11677 0.11118 -0.1098 0.1122 1.0000
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Polar data table (+)
Polar graphs
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