MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 114 13.02% (mh114-il) Reynolds number: 500,000 Max Cl/Cd: 131.16 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh114-il-500000.txt Download as CSV file: xf-mh114-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 114 13.02%
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0364 0.11305 0.11060 -0.0975 0.9687 0.0165
-10.750 -0.0270 0.10851 0.10606 -0.1027 0.9657 0.0169
-10.500 -0.0147 0.10417 0.10171 -0.1076 0.9637 0.0170
-10.250 0.0001 0.09984 0.09739 -0.1115 0.9622 0.0171
-10.000 0.0120 0.09728 0.09483 -0.1115 0.9559 0.0173
-9.750 0.0297 0.09427 0.09182 -0.1139 0.9530 0.0175
-9.500 0.0490 0.09110 0.08864 -0.1174 0.9507 0.0180
-9.250 0.0664 0.08766 0.08518 -0.1214 0.9467 0.0182
-9.000 0.0842 0.08406 0.08158 -0.1256 0.9415 0.0189
-8.750 0.1052 0.07866 0.07615 -0.1340 0.9378 0.0204
-8.500 0.1214 0.07225 0.06971 -0.1435 0.9297 0.0207
-8.250 0.1426 0.06918 0.06662 -0.1467 0.9239 0.0210
-8.000 0.1630 0.06655 0.06396 -0.1500 0.9160 0.0213
-7.750 0.1814 0.06382 0.06117 -0.1534 0.9070 0.0218
-7.500 0.1908 0.06124 0.05855 -0.1552 0.8958 0.0224
-7.250 0.1974 0.05828 0.05556 -0.1572 0.8851 0.0231
-6.750 0.1709 0.03884 0.03580 -0.1797 0.8558 0.0251
-6.500 0.1539 0.02327 0.01916 -0.1880 0.8442 0.0142
-6.250 0.1767 0.02057 0.01611 -0.1892 0.8385 0.0132
-6.000 0.2002 0.01781 0.01289 -0.1901 0.8323 0.0127
-5.750 0.2280 0.01580 0.01044 -0.1909 0.8274 0.0126
-5.500 0.2550 0.01460 0.00898 -0.1911 0.8221 0.0128
-5.250 0.2822 0.01372 0.00789 -0.1911 0.8164 0.0134
-5.000 0.3109 0.01283 0.00682 -0.1915 0.8115 0.0142
-4.750 0.3386 0.01231 0.00627 -0.1917 0.8064 0.0152
-4.500 0.3662 0.01186 0.00574 -0.1917 0.8007 0.0165
-4.250 0.3954 0.01132 0.00512 -0.1922 0.7957 0.0180
-4.000 0.4238 0.01106 0.00480 -0.1923 0.7905 0.0210
-3.750 0.4517 0.01075 0.00447 -0.1924 0.7847 0.0250
-3.500 0.4813 0.01033 0.00402 -0.1928 0.7796 0.0317
-3.250 0.5099 0.01006 0.00375 -0.1930 0.7743 0.0440
-3.000 0.5380 0.00978 0.00351 -0.1932 0.7683 0.0625
-2.750 0.5675 0.00953 0.00332 -0.1936 0.7631 0.0918
-2.500 0.5956 0.00932 0.00321 -0.1938 0.7574 0.1322
-2.250 0.6237 0.00912 0.00313 -0.1940 0.7514 0.1792
-2.000 0.6531 0.00898 0.00305 -0.1944 0.7460 0.2316
-1.750 0.6805 0.00883 0.00303 -0.1944 0.7398 0.2826
-1.500 0.7086 0.00871 0.00300 -0.1945 0.7337 0.3332
-1.250 0.7373 0.00864 0.00299 -0.1948 0.7281 0.3856
-1.000 0.7645 0.00854 0.00302 -0.1947 0.7214 0.4388
-0.750 0.7927 0.00850 0.00302 -0.1948 0.7153 0.4886
-0.500 0.8201 0.00845 0.00307 -0.1947 0.7089 0.5345
-0.250 0.8473 0.00843 0.00310 -0.1945 0.7020 0.5765
0.000 0.8748 0.00843 0.00314 -0.1944 0.6957 0.6176
0.250 0.9011 0.00841 0.00320 -0.1941 0.6882 0.6574
0.750 0.9535 0.00841 0.00332 -0.1933 0.6739 0.7369
1.000 0.9789 0.00843 0.00338 -0.1927 0.6667 0.7791
1.250 1.0022 0.00840 0.00346 -0.1916 0.6588 0.8266
1.500 1.0214 0.00836 0.00349 -0.1895 0.6513 0.8880
1.750 1.0427 0.00827 0.00346 -0.1880 0.6433 1.0000
2.000 1.0695 0.00841 0.00351 -0.1878 0.6351 1.0000
2.250 1.0958 0.00853 0.00359 -0.1876 0.6263 1.0000
2.500 1.1218 0.00870 0.00366 -0.1873 0.6179 1.0000
2.750 1.1475 0.00882 0.00376 -0.1869 0.6085 1.0000
3.000 1.1728 0.00899 0.00386 -0.1865 0.5997 1.0000
3.250 1.1977 0.00915 0.00399 -0.1860 0.5898 1.0000
3.500 1.2224 0.00932 0.00411 -0.1854 0.5803 1.0000
4.000 1.2703 0.00970 0.00440 -0.1841 0.5601 1.0000
4.250 1.2936 0.00991 0.00457 -0.1833 0.5500 1.0000
4.500 1.3161 0.01015 0.00475 -0.1823 0.5395 1.0000
4.750 1.3389 0.01036 0.00494 -0.1814 0.5287 1.0000
5.000 1.3606 0.01060 0.00514 -0.1804 0.5181 1.0000
5.500 1.4015 0.01111 0.00559 -0.1777 0.4962 1.0000
5.750 1.4206 0.01139 0.00583 -0.1762 0.4855 1.0000
6.000 1.4384 0.01173 0.00612 -0.1744 0.4748 1.0000
6.250 1.4574 0.01201 0.00640 -0.1728 0.4634 1.0000
6.500 1.4758 0.01234 0.00670 -0.1712 0.4529 1.0000
6.750 1.4926 0.01273 0.00705 -0.1693 0.4421 1.0000
7.000 1.5108 0.01308 0.00739 -0.1677 0.4312 1.0000
7.250 1.5281 0.01346 0.00776 -0.1660 0.4206 1.0000
7.500 1.5439 0.01392 0.00818 -0.1641 0.4101 1.0000
7.750 1.5606 0.01434 0.00861 -0.1623 0.3994 1.0000
8.000 1.5769 0.01480 0.00906 -0.1605 0.3890 1.0000
8.250 1.5912 0.01536 0.00958 -0.1585 0.3786 1.0000
8.500 1.6069 0.01587 0.01010 -0.1567 0.3680 1.0000
8.750 1.6220 0.01642 0.01066 -0.1548 0.3580 1.0000
9.000 1.6348 0.01710 0.01131 -0.1527 0.3478 1.0000
9.250 1.6493 0.01771 0.01193 -0.1509 0.3371 1.0000
9.500 1.6629 0.01839 0.01262 -0.1490 0.3269 1.0000
9.750 1.6740 0.01922 0.01343 -0.1468 0.3165 1.0000
10.000 1.6875 0.01995 0.01418 -0.1450 0.3063 1.0000
10.250 1.6995 0.02080 0.01503 -0.1431 0.2960 1.0000
10.500 1.7091 0.02180 0.01602 -0.1409 0.2857 1.0000
10.750 1.7203 0.02276 0.01699 -0.1391 0.2747 1.0000
11.000 1.7310 0.02377 0.01801 -0.1372 0.2642 1.0000
11.250 1.7394 0.02496 0.01919 -0.1352 0.2539 1.0000
11.500 1.7477 0.02620 0.02043 -0.1332 0.2433 1.0000
11.750 1.7570 0.02741 0.02167 -0.1314 0.2326 1.0000
12.000 1.7641 0.02882 0.02308 -0.1295 0.2222 1.0000
12.250 1.7692 0.03044 0.02468 -0.1275 0.2116 1.0000
12.500 1.7763 0.03195 0.02621 -0.1259 0.2010 1.0000
12.750 1.7824 0.03358 0.02785 -0.1242 0.1909 1.0000
13.000 1.7863 0.03546 0.02974 -0.1224 0.1810 1.0000
13.250 1.7894 0.03748 0.03175 -0.1207 0.1710 1.0000
13.500 1.7941 0.03940 0.03370 -0.1193 0.1611 1.0000
13.750 1.7968 0.04157 0.03588 -0.1178 0.1519 1.0000
14.000 1.7971 0.04406 0.03836 -0.1163 0.1430 1.0000
14.250 1.8010 0.04625 0.04059 -0.1152 0.1346 1.0000
14.500 1.8017 0.04884 0.04320 -0.1140 0.1270 1.0000
14.750 1.8020 0.05154 0.04593 -0.1129 0.1192 1.0000
15.000 1.8034 0.05420 0.04863 -0.1120 0.1120 1.0000
15.250 1.8004 0.05745 0.05189 -0.1112 0.1049 1.0000
15.500 1.8015 0.06029 0.05479 -0.1105 0.0979 1.0000
15.750 1.7980 0.06376 0.05829 -0.1100 0.0917 1.0000
16.000 1.7968 0.06704 0.06161 -0.1096 0.0854 1.0000
16.250 1.7930 0.07073 0.06536 -0.1093 0.0799 1.0000
16.500 1.7901 0.07438 0.06906 -0.1092 0.0744 1.0000
16.750 1.7852 0.07839 0.07312 -0.1092 0.0695 1.0000
17.000 1.7814 0.08231 0.07711 -0.1094 0.0647 1.0000
17.250 1.7746 0.08676 0.08162 -0.1097 0.0605 1.0000
17.500 1.7708 0.09084 0.08577 -0.1102 0.0563 1.0000
18.000 1.7579 0.09996 0.09503 -0.1117 0.0488 1.0000
18.250 1.7489 0.10502 0.10015 -0.1128 0.0454 1.0000
18.500 1.7432 0.10961 0.10483 -0.1140 0.0423 1.0000
18.750 1.7355 0.11456 0.10985 -0.1153 0.0392 1.0000
19.000 1.7270 0.11971 0.11507 -0.1169 0.0364 1.0000
19.250 1.7214 0.12436 0.11982 -0.1185 0.0339 1.0000
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Polar data table (+)
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