MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 113 14.62% (mh113-il) Reynolds number: 500,000 Max Cl/Cd: 124.29 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh113-il-500000.txt Download as CSV file: xf-mh113-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 0.1587 0.09450 0.09197 -0.1304 0.9341 0.0248
-11.250 0.1731 0.09053 0.08796 -0.1341 0.9304 0.0258
-11.000 0.1622 0.08440 0.08181 -0.1392 0.9224 0.0268
-10.750 0.1825 0.08142 0.07879 -0.1407 0.9167 0.0271
-10.500 0.1993 0.07907 0.07640 -0.1417 0.9090 0.0275
-10.250 0.2117 0.07629 0.07357 -0.1432 0.9012 0.0279
-10.000 0.2210 0.07367 0.07092 -0.1443 0.8933 0.0287
-9.750 0.1595 0.08367 0.08097 -0.1452 0.9245 0.0278
-9.500 0.1818 0.08046 0.07771 -0.1498 0.9174 0.0286
-9.250 0.1978 0.07728 0.07448 -0.1536 0.9081 0.0295
-9.000 0.1914 0.07032 0.06746 -0.1608 0.8947 0.0313
-8.750 0.2076 0.06909 0.06618 -0.1607 0.8861 0.0316
-8.500 0.2230 0.06768 0.06473 -0.1612 0.8781 0.0322
-8.250 0.2302 0.06550 0.06252 -0.1618 0.8686 0.0327
-8.000 0.2362 0.06319 0.06017 -0.1627 0.8600 0.0337
-7.750 0.1986 0.05404 0.05100 -0.1687 0.8464 0.0361
-7.500 0.2028 0.05281 0.04979 -0.1672 0.8386 0.0363
-7.250 0.0987 0.02386 0.01933 -0.1899 0.8204 0.0227
-7.000 0.1188 0.02128 0.01641 -0.1908 0.8153 0.0224
-6.750 0.1416 0.01933 0.01412 -0.1913 0.8103 0.0223
-6.500 0.1654 0.01787 0.01240 -0.1914 0.8048 0.0224
-6.250 0.1916 0.01674 0.01101 -0.1916 0.8000 0.0226
-6.000 0.2200 0.01593 0.00995 -0.1920 0.7955 0.0228
-5.750 0.2452 0.01506 0.00896 -0.1918 0.7903 0.0231
-5.500 0.2714 0.01413 0.00798 -0.1918 0.7853 0.0235
-5.250 0.2996 0.01358 0.00737 -0.1921 0.7806 0.0241
-5.000 0.3271 0.01317 0.00691 -0.1921 0.7759 0.0249
-4.750 0.3542 0.01279 0.00648 -0.1920 0.7706 0.0260
-4.500 0.3824 0.01246 0.00604 -0.1921 0.7656 0.0268
-4.250 0.4115 0.01190 0.00544 -0.1926 0.7610 0.0279
-4.000 0.4385 0.01157 0.00512 -0.1924 0.7557 0.0292
-3.750 0.4666 0.01129 0.00479 -0.1925 0.7504 0.0308
-3.500 0.4962 0.01097 0.00441 -0.1929 0.7456 0.0332
-3.250 0.5241 0.01072 0.00415 -0.1929 0.7403 0.0369
-3.000 0.5522 0.01045 0.00391 -0.1930 0.7347 0.0465
-2.750 0.5816 0.01011 0.00366 -0.1934 0.7296 0.0790
-2.500 0.6099 0.00994 0.00355 -0.1936 0.7243 0.1074
-2.250 0.6375 0.00978 0.00347 -0.1936 0.7184 0.1371
-2.000 0.6661 0.00965 0.00339 -0.1938 0.7130 0.1722
-1.750 0.6943 0.00952 0.00336 -0.1939 0.7074 0.2135
-1.500 0.7218 0.00938 0.00335 -0.1939 0.7013 0.2628
-1.250 0.7503 0.00928 0.00333 -0.1941 0.6956 0.3125
-1.000 0.7780 0.00921 0.00335 -0.1941 0.6897 0.3564
-0.750 0.8052 0.00914 0.00336 -0.1940 0.6831 0.3978
-0.500 0.8334 0.00913 0.00337 -0.1941 0.6772 0.4404
-0.250 0.8602 0.00908 0.00343 -0.1939 0.6706 0.4830
0.000 0.8872 0.00907 0.00346 -0.1937 0.6639 0.5230
0.250 0.9144 0.00909 0.00352 -0.1935 0.6576 0.5618
0.500 0.9407 0.00908 0.00359 -0.1931 0.6503 0.5982
0.750 0.9674 0.00913 0.00364 -0.1929 0.6436 0.6344
1.000 0.9931 0.00913 0.00373 -0.1924 0.6363 0.6702
1.250 1.0186 0.00917 0.00380 -0.1919 0.6289 0.7071
1.500 1.0436 0.00919 0.00390 -0.1912 0.6217 0.7457
1.750 1.0673 0.00921 0.00400 -0.1903 0.6139 0.7889
2.000 1.0888 0.00922 0.00409 -0.1888 0.6066 0.8420
2.250 1.1033 0.00906 0.00409 -0.1857 0.5988 0.9624
2.500 1.1298 0.00922 0.00415 -0.1855 0.5910 1.0000
2.750 1.1551 0.00935 0.00425 -0.1851 0.5824 1.0000
3.000 1.1798 0.00954 0.00436 -0.1845 0.5745 1.0000
3.250 1.2043 0.00969 0.00448 -0.1839 0.5657 1.0000
3.500 1.2280 0.00990 0.00461 -0.1832 0.5575 1.0000
3.750 1.2516 0.01007 0.00475 -0.1824 0.5485 1.0000
4.000 1.2743 0.01029 0.00491 -0.1815 0.5400 1.0000
4.250 1.2967 0.01049 0.00507 -0.1805 0.5309 1.0000
4.500 1.3175 0.01072 0.00525 -0.1792 0.5223 1.0000
4.750 1.3376 0.01093 0.00543 -0.1778 0.5131 1.0000
5.000 1.3572 0.01118 0.00564 -0.1763 0.5044 1.0000
5.250 1.3762 0.01145 0.00586 -0.1747 0.4952 1.0000
5.500 1.3957 0.01172 0.00611 -0.1733 0.4864 1.0000
5.750 1.4136 0.01204 0.00638 -0.1715 0.4771 1.0000
6.000 1.4327 0.01232 0.00665 -0.1701 0.4682 1.0000
6.250 1.4496 0.01270 0.00697 -0.1682 0.4592 1.0000
6.500 1.4683 0.01301 0.00728 -0.1667 0.4502 1.0000
7.000 1.5026 0.01377 0.00800 -0.1633 0.4325 1.0000
7.250 1.5178 0.01425 0.00843 -0.1614 0.4238 1.0000
7.500 1.5352 0.01465 0.00884 -0.1598 0.4149 1.0000
7.750 1.5499 0.01517 0.00932 -0.1578 0.4065 1.0000
8.000 1.5665 0.01563 0.00979 -0.1562 0.3979 1.0000
8.250 1.5806 0.01621 0.01034 -0.1542 0.3897 1.0000
8.500 1.5965 0.01673 0.01087 -0.1526 0.3813 1.0000
8.750 1.6098 0.01739 0.01150 -0.1506 0.3732 1.0000
9.000 1.6249 0.01797 0.01211 -0.1490 0.3649 1.0000
9.250 1.6374 0.01871 0.01283 -0.1470 0.3571 1.0000
9.500 1.6519 0.01937 0.01351 -0.1454 0.3488 1.0000
9.750 1.6634 0.02022 0.01432 -0.1434 0.3411 1.0000
10.000 1.6775 0.02094 0.01508 -0.1418 0.3329 1.0000
10.250 1.6876 0.02190 0.01602 -0.1398 0.3252 1.0000
10.500 1.7015 0.02269 0.01685 -0.1384 0.3174 1.0000
10.750 1.7102 0.02380 0.01793 -0.1363 0.3096 1.0000
11.000 1.7240 0.02464 0.01882 -0.1349 0.3021 1.0000
11.250 1.7314 0.02590 0.02005 -0.1329 0.2941 1.0000
11.500 1.7445 0.02683 0.02104 -0.1316 0.2867 1.0000
11.750 1.7513 0.02821 0.02239 -0.1297 0.2788 1.0000
12.000 1.7631 0.02929 0.02353 -0.1283 0.2713 1.0000
12.250 1.7694 0.03079 0.02502 -0.1265 0.2637 1.0000
12.500 1.7798 0.03204 0.02631 -0.1252 0.2561 1.0000
12.750 1.7855 0.03368 0.02794 -0.1235 0.2484 1.0000
13.000 1.7944 0.03511 0.02943 -0.1222 0.2410 1.0000
13.250 1.7992 0.03692 0.03123 -0.1207 0.2333 1.0000
13.500 1.8070 0.03854 0.03289 -0.1194 0.2259 1.0000
13.750 1.8106 0.04056 0.03491 -0.1180 0.2183 1.0000
14.000 1.8176 0.04232 0.03672 -0.1169 0.2111 1.0000
14.250 1.8198 0.04458 0.03898 -0.1156 0.2036 1.0000
14.500 1.8255 0.04656 0.04101 -0.1146 0.1967 1.0000
14.750 1.8271 0.04901 0.04346 -0.1134 0.1894 1.0000
15.000 1.8310 0.05128 0.04578 -0.1125 0.1827 1.0000
15.250 1.8319 0.05390 0.04842 -0.1116 0.1757 1.0000
15.500 1.8342 0.05644 0.05101 -0.1108 0.1693 1.0000
15.750 1.8345 0.05928 0.05388 -0.1101 0.1627 1.0000
16.000 1.8344 0.06221 0.05684 -0.1095 0.1567 1.0000
16.250 1.8356 0.06506 0.05974 -0.1090 0.1505 1.0000
16.500 1.8315 0.06860 0.06330 -0.1086 0.1448 1.0000
16.750 1.8331 0.07150 0.06628 -0.1083 0.1388 1.0000
17.000 1.8276 0.07538 0.07017 -0.1081 0.1332 1.0000
17.250 1.8285 0.07848 0.07335 -0.1081 0.1278 1.0000
17.500 1.8235 0.08243 0.07734 -0.1082 0.1224 1.0000
17.750 1.8200 0.08621 0.08117 -0.1084 0.1176 1.0000
18.000 1.8181 0.08983 0.08486 -0.1087 0.1127 1.0000
18.250 1.8096 0.09447 0.08952 -0.1092 0.1081 1.0000
18.500 1.8087 0.09803 0.09317 -0.1097 0.1038 1.0000
18.750 1.8029 0.10234 0.09754 -0.1105 0.0994 1.0000
19.000 1.7955 0.10694 0.10218 -0.1114 0.0955 1.0000
19.250 1.7942 0.11064 0.10597 -0.1122 0.0917 1.0000
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Polar data table (+)
Polar graphs
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