MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 112 Airfoil (mh112-il) Reynolds number: 500,000 Max Cl/Cd: 109.72 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh112-il-500000-n5.txt Download as CSV file: xf-mh112-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 112 Airfoil
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
------ -------- --------- --------- -------- -------- --------
-11.750 0.1965 0.09912 0.09565 -0.1543 0.8480 0.0125
-10.750 -0.0517 0.04432 0.04027 -0.1757 0.8119 0.0117
-10.500 -0.0943 0.03587 0.03150 -0.1810 0.8022 0.0115
-10.250 -0.1124 0.03141 0.02693 -0.1835 0.7944 0.0115
-10.000 -0.1228 0.02734 0.02262 -0.1883 0.7864 0.0115
-9.750 -0.1159 0.02511 0.02018 -0.1902 0.7807 0.0116
-9.500 -0.1027 0.02353 0.01845 -0.1909 0.7754 0.0117
-9.250 -0.0860 0.02220 0.01696 -0.1914 0.7701 0.0117
-9.000 -0.0662 0.02112 0.01573 -0.1918 0.7653 0.0118
-8.750 -0.0451 0.02010 0.01457 -0.1920 0.7610 0.0119
-8.500 -0.0228 0.01919 0.01354 -0.1922 0.7564 0.0120
-8.250 0.0006 0.01836 0.01259 -0.1924 0.7515 0.0121
-8.000 0.0249 0.01764 0.01174 -0.1926 0.7470 0.0122
-7.750 0.0500 0.01697 0.01095 -0.1927 0.7430 0.0123
-7.500 0.0755 0.01634 0.01024 -0.1929 0.7385 0.0124
-7.250 0.1014 0.01576 0.00957 -0.1930 0.7338 0.0126
-7.000 0.1277 0.01523 0.00894 -0.1931 0.7294 0.0128
-6.750 0.1545 0.01477 0.00836 -0.1932 0.7252 0.0129
-6.500 0.1814 0.01430 0.00783 -0.1933 0.7209 0.0132
-6.250 0.2086 0.01388 0.00734 -0.1935 0.7163 0.0135
-6.000 0.2359 0.01351 0.00688 -0.1935 0.7117 0.0138
-5.750 0.2635 0.01319 0.00646 -0.1936 0.7073 0.0141
-5.500 0.2913 0.01279 0.00603 -0.1938 0.7032 0.0145
-5.250 0.3191 0.01250 0.00571 -0.1940 0.6986 0.0150
-5.000 0.3469 0.01225 0.00540 -0.1940 0.6938 0.0156
-4.750 0.3747 0.01204 0.00511 -0.1941 0.6892 0.0164
-4.500 0.4029 0.01181 0.00484 -0.1942 0.6850 0.0173
-4.250 0.4309 0.01160 0.00461 -0.1943 0.6803 0.0186
-4.000 0.4588 0.01143 0.00439 -0.1943 0.6754 0.0202
-3.750 0.4866 0.01128 0.00419 -0.1943 0.6706 0.0225
-3.500 0.5147 0.01111 0.00402 -0.1943 0.6660 0.0261
-3.250 0.5427 0.01096 0.00388 -0.1944 0.6612 0.0319
-3.000 0.5705 0.01083 0.00376 -0.1944 0.6561 0.0412
-2.750 0.5981 0.01073 0.00365 -0.1944 0.6513 0.0521
-2.500 0.6261 0.01060 0.00357 -0.1945 0.6463 0.0656
-2.250 0.6537 0.01050 0.00350 -0.1945 0.6411 0.0811
-2.000 0.6811 0.01042 0.00344 -0.1944 0.6360 0.0997
-1.750 0.7087 0.01033 0.00341 -0.1944 0.6310 0.1233
-1.500 0.7363 0.01025 0.00339 -0.1944 0.6255 0.1494
-1.250 0.7634 0.01019 0.00338 -0.1943 0.6201 0.1763
-1.000 0.7902 0.01018 0.00338 -0.1942 0.6150 0.2020
-0.750 0.8177 0.01013 0.00340 -0.1941 0.6095 0.2292
-0.500 0.8444 0.01012 0.00342 -0.1939 0.6037 0.2572
-0.250 0.8704 0.01013 0.00346 -0.1936 0.5980 0.2872
0.000 0.8972 0.01012 0.00351 -0.1934 0.5922 0.3193
0.250 0.9229 0.01015 0.00357 -0.1931 0.5852 0.3499
0.500 0.9478 0.01020 0.00365 -0.1925 0.5784 0.3819
0.750 0.9735 0.01024 0.00373 -0.1921 0.5712 0.4135
1.000 0.9978 0.01031 0.00383 -0.1915 0.5641 0.4426
1.250 1.0227 0.01038 0.00394 -0.1909 0.5580 0.4724
1.500 1.0474 0.01046 0.00405 -0.1903 0.5514 0.4994
1.750 1.0705 0.01058 0.00417 -0.1894 0.5451 0.5239
2.000 1.0943 0.01067 0.00430 -0.1886 0.5392 0.5489
2.250 1.1170 0.01076 0.00443 -0.1877 0.5329 0.5723
2.500 1.1379 0.01090 0.00457 -0.1863 0.5268 0.5955
2.750 1.1606 0.01101 0.00472 -0.1854 0.5209 0.6198
3.000 1.1823 0.01115 0.00490 -0.1842 0.5143 0.6461
3.250 1.2025 0.01133 0.00510 -0.1828 0.5082 0.6725
3.500 1.2248 0.01145 0.00530 -0.1818 0.5022 0.7041
3.750 1.2448 0.01160 0.00552 -0.1804 0.4954 0.7432
4.000 1.2627 0.01175 0.00577 -0.1785 0.4894 0.7950
4.250 1.2760 0.01163 0.00591 -0.1755 0.4834 0.9701
4.500 1.2958 0.01190 0.00613 -0.1742 0.4764 1.0000
4.750 1.3157 0.01220 0.00638 -0.1729 0.4701 1.0000
5.000 1.3363 0.01247 0.00663 -0.1717 0.4633 1.0000
5.250 1.3540 0.01283 0.00695 -0.1701 0.4561 1.0000
5.500 1.3738 0.01314 0.00724 -0.1689 0.4491 1.0000
5.750 1.3914 0.01353 0.00759 -0.1673 0.4413 1.0000
6.000 1.4092 0.01392 0.00795 -0.1658 0.4345 1.0000
6.250 1.4267 0.01434 0.00834 -0.1643 0.4262 1.0000
6.500 1.4423 0.01484 0.00881 -0.1625 0.4185 1.0000
6.750 1.4596 0.01529 0.00925 -0.1611 0.4100 1.0000
7.000 1.4735 0.01588 0.00980 -0.1591 0.4017 1.0000
7.250 1.4896 0.01642 0.01032 -0.1576 0.3925 1.0000
7.500 1.5028 0.01710 0.01096 -0.1556 0.3839 1.0000
7.750 1.5177 0.01772 0.01157 -0.1540 0.3748 1.0000
8.000 1.5300 0.01849 0.01230 -0.1521 0.3658 1.0000
8.250 1.5431 0.01925 0.01304 -0.1503 0.3563 1.0000
8.500 1.5550 0.02010 0.01387 -0.1485 0.3473 1.0000
8.750 1.5664 0.02100 0.01475 -0.1466 0.3381 1.0000
9.000 1.5784 0.02190 0.01563 -0.1449 0.3299 1.0000
9.250 1.5886 0.02294 0.01664 -0.1430 0.3210 1.0000
9.500 1.6006 0.02390 0.01760 -0.1414 0.3140 1.0000
9.750 1.6114 0.02496 0.01865 -0.1398 0.3061 1.0000
10.000 1.6216 0.02609 0.01977 -0.1381 0.2992 1.0000
10.250 1.6329 0.02718 0.02086 -0.1366 0.2918 1.0000
10.500 1.6410 0.02852 0.02218 -0.1349 0.2850 1.0000
10.750 1.6536 0.02957 0.02326 -0.1336 0.2788 1.0000
11.000 1.6620 0.03096 0.02465 -0.1321 0.2720 1.0000
11.250 1.6722 0.03225 0.02595 -0.1307 0.2662 1.0000
11.500 1.6823 0.03357 0.02729 -0.1295 0.2599 1.0000
11.750 1.6897 0.03515 0.02887 -0.1280 0.2539 1.0000
12.000 1.7001 0.03651 0.03026 -0.1269 0.2482 1.0000
12.250 1.7089 0.03803 0.03180 -0.1257 0.2421 1.0000
12.500 1.7150 0.03983 0.03360 -0.1244 0.2362 1.0000
12.750 1.7252 0.04130 0.03510 -0.1234 0.2304 1.0000
13.000 1.7307 0.04322 0.03704 -0.1222 0.2246 1.0000
13.250 1.7388 0.04494 0.03878 -0.1212 0.2192 1.0000
13.500 1.7454 0.04684 0.04071 -0.1202 0.2130 1.0000
13.750 1.7495 0.04902 0.04289 -0.1191 0.2075 1.0000
14.000 1.7572 0.05088 0.04480 -0.1183 0.2018 1.0000
14.250 1.7616 0.05311 0.04705 -0.1175 0.1958 1.0000
14.500 1.7661 0.05538 0.04935 -0.1167 0.1906 1.0000
14.750 1.7718 0.05753 0.05153 -0.1160 0.1850 1.0000
15.000 1.7724 0.06032 0.05434 -0.1152 0.1795 1.0000
15.250 1.7789 0.06245 0.05652 -0.1147 0.1745 1.0000
15.500 1.7811 0.06515 0.05925 -0.1141 0.1692 1.0000
15.750 1.7832 0.06787 0.06200 -0.1136 0.1641 1.0000
16.000 1.7860 0.07055 0.06473 -0.1132 0.1588 1.0000
16.250 1.7862 0.07360 0.06780 -0.1129 0.1540 1.0000
16.500 1.7888 0.07639 0.07065 -0.1127 0.1495 1.0000
16.750 1.7904 0.07933 0.07363 -0.1125 0.1446 1.0000
17.000 1.7887 0.08276 0.07709 -0.1124 0.1403 1.0000
17.250 1.7917 0.08556 0.07996 -0.1124 0.1362 1.0000
17.500 1.7914 0.08885 0.08330 -0.1125 0.1318 1.0000
17.750 1.7895 0.09241 0.08689 -0.1126 0.1280 1.0000
18.000 1.7915 0.09542 0.08997 -0.1129 0.1241 1.0000
18.250 1.7896 0.09903 0.09363 -0.1132 0.1200 1.0000
18.500 1.7883 0.10255 0.09719 -0.1136 0.1166 1.0000
18.750 1.7883 0.10590 0.10062 -0.1141 0.1129 1.0000
19.000 1.7865 0.10952 0.10428 -0.1147 0.1092 1.0000
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