MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 112 Airfoil (mh112-il) Reynolds number: 200,000 Max Cl/Cd: 79.96 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh112-il-200000.txt Download as CSV file: xf-mh112-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.1936 0.10020 0.09621 -0.1438 0.9301 0.0510
-10.000 0.2032 0.09782 0.09384 -0.1448 0.9227 0.0525
-9.750 0.2001 0.09376 0.08977 -0.1534 0.9168 0.0551
-9.500 0.2362 0.09056 0.08653 -0.1537 0.9151 0.0563
-9.250 0.2517 0.08807 0.08403 -0.1553 0.9094 0.0577
-9.000 0.2604 0.08550 0.08145 -0.1572 0.9021 0.0599
-8.750 0.2614 0.08131 0.07723 -0.1638 0.8961 0.0618
-8.500 0.2742 0.07967 0.07560 -0.1617 0.8888 0.0625
-8.250 0.2898 0.07749 0.07340 -0.1624 0.8827 0.0638
-8.000 0.3040 0.07477 0.07064 -0.1651 0.8778 0.0662
-7.750 0.2674 0.07179 0.06774 -0.1672 0.8645 0.0687
-7.500 0.2961 0.06963 0.06553 -0.1664 0.8613 0.0695
-7.250 0.3116 0.06787 0.06375 -0.1662 0.8563 0.0708
-7.000 0.3108 0.06639 0.06231 -0.1645 0.8479 0.0724
-6.500 0.2721 0.06054 0.05654 -0.1669 0.8300 0.0770
-6.250 0.2124 0.03721 0.03229 -0.1882 0.8202 0.0445
-6.000 0.2029 0.03163 0.02590 -0.1877 0.8103 0.0389
-5.750 0.2291 0.02903 0.02299 -0.1892 0.8062 0.0384
-5.500 0.2611 0.02651 0.02003 -0.1913 0.8031 0.0381
-5.250 0.2871 0.02482 0.01795 -0.1918 0.7987 0.0383
-5.000 0.3059 0.02377 0.01662 -0.1905 0.7919 0.0388
-4.750 0.3359 0.02250 0.01518 -0.1911 0.7878 0.0398
-4.500 0.3696 0.02153 0.01413 -0.1922 0.7847 0.0418
-4.250 0.4055 0.02064 0.01308 -0.1937 0.7819 0.0451
-4.000 0.4191 0.02051 0.01298 -0.1913 0.7741 0.0481
-3.750 0.4483 0.01980 0.01227 -0.1916 0.7696 0.0522
-3.500 0.4821 0.01903 0.01146 -0.1926 0.7662 0.0587
-3.250 0.5188 0.01836 0.01078 -0.1943 0.7633 0.0716
-3.000 0.5356 0.01820 0.01072 -0.1925 0.7561 0.0864
-2.750 0.5649 0.01775 0.01036 -0.1929 0.7511 0.1116
-2.500 0.5992 0.01731 0.00995 -0.1942 0.7474 0.1453
-2.250 0.6360 0.01690 0.00961 -0.1959 0.7444 0.1857
-2.000 0.6533 0.01697 0.00980 -0.1942 0.7372 0.2194
-1.750 0.6822 0.01674 0.00969 -0.1944 0.7321 0.2630
-1.500 0.7163 0.01644 0.00946 -0.1956 0.7283 0.3119
-1.250 0.7502 0.01627 0.00935 -0.1967 0.7248 0.3618
-1.000 0.7682 0.01640 0.00963 -0.1949 0.7176 0.4013
-0.750 0.7973 0.01629 0.00959 -0.1950 0.7126 0.4474
-0.500 0.8313 0.01614 0.00945 -0.1959 0.7088 0.4937
-0.250 0.8570 0.01623 0.00960 -0.1954 0.7037 0.5327
0.000 0.8790 0.01632 0.00976 -0.1943 0.6972 0.5685
0.250 0.9092 0.01622 0.00968 -0.1944 0.6926 0.6055
0.500 0.9433 0.01610 0.00953 -0.1953 0.6889 0.6421
0.750 0.9599 0.01629 0.00985 -0.1931 0.6818 0.6733
1.000 0.9852 0.01624 0.00984 -0.1924 0.6761 0.7081
1.250 1.0161 0.01606 0.00966 -0.1925 0.6717 0.7464
1.500 1.0343 0.01612 0.00983 -0.1905 0.6654 0.7860
1.750 1.0509 0.01603 0.00985 -0.1879 0.6590 0.8368
2.000 1.0747 0.01563 0.00949 -0.1864 0.6542 1.0000
2.250 1.1035 0.01582 0.00957 -0.1868 0.6482 1.0000
2.500 1.1282 0.01599 0.00969 -0.1865 0.6414 1.0000
2.750 1.1616 0.01602 0.00956 -0.1875 0.6362 1.0000
3.000 1.1882 0.01622 0.00969 -0.1874 0.6304 1.0000
3.250 1.2103 0.01643 0.00988 -0.1865 0.6236 1.0000
3.500 1.2419 0.01648 0.00981 -0.1872 0.6182 1.0000
3.750 1.2672 0.01671 0.00998 -0.1868 0.6123 1.0000
4.000 1.2881 0.01693 0.01020 -0.1856 0.6053 1.0000
4.250 1.3191 0.01701 0.01017 -0.1862 0.5997 1.0000
4.500 1.3411 0.01728 0.01043 -0.1852 0.5933 1.0000
4.750 1.3623 0.01750 0.01063 -0.1841 0.5863 1.0000
5.000 1.3941 0.01759 0.01060 -0.1849 0.5806 1.0000
5.250 1.4099 0.01793 0.01099 -0.1828 0.5733 1.0000
5.500 1.4328 0.01812 0.01114 -0.1820 0.5664 1.0000
5.750 1.4625 0.01829 0.01122 -0.1824 0.5604 1.0000
6.000 1.4738 0.01865 0.01164 -0.1796 0.5524 1.0000
6.250 1.5003 0.01881 0.01173 -0.1794 0.5458 1.0000
6.500 1.5157 0.01916 0.01210 -0.1773 0.5384 1.0000
6.750 1.5314 0.01942 0.01235 -0.1752 0.5308 1.0000
7.000 1.5561 0.01967 0.01253 -0.1747 0.5238 1.0000
7.250 1.5621 0.02010 0.01303 -0.1710 0.5156 1.0000
7.500 1.5904 0.02029 0.01310 -0.1712 0.5084 1.0000
7.750 1.5920 0.02086 0.01377 -0.1669 0.4999 1.0000
8.000 1.6121 0.02116 0.01400 -0.1657 0.4921 1.0000
8.250 1.6193 0.02175 0.01464 -0.1625 0.4836 1.0000
8.500 1.6343 0.02218 0.01503 -0.1606 0.4754 1.0000
8.750 1.6439 0.02280 0.01568 -0.1580 0.4669 1.0000
9.000 1.6554 0.02337 0.01624 -0.1557 0.4582 1.0000
9.250 1.6651 0.02408 0.01696 -0.1533 0.4495 1.0000
9.500 1.6750 0.02477 0.01764 -0.1509 0.4407 1.0000
9.750 1.6837 0.02560 0.01848 -0.1485 0.4319 1.0000
10.000 1.6932 0.02639 0.01927 -0.1462 0.4231 1.0000
10.250 1.7006 0.02736 0.02026 -0.1438 0.4143 1.0000
10.500 1.7098 0.02826 0.02115 -0.1417 0.4056 1.0000
10.750 1.7163 0.02936 0.02228 -0.1394 0.3969 1.0000
11.000 1.7252 0.03037 0.02328 -0.1374 0.3884 1.0000
11.250 1.7314 0.03159 0.02453 -0.1352 0.3799 1.0000
11.500 1.7391 0.03274 0.02566 -0.1333 0.3716 1.0000
11.750 1.7457 0.03404 0.02699 -0.1313 0.3634 1.0000
12.000 1.7521 0.03535 0.02832 -0.1294 0.3553 1.0000
12.250 1.7601 0.03666 0.02964 -0.1278 0.3476 1.0000
12.500 1.7642 0.03822 0.03124 -0.1259 0.3397 1.0000
12.750 1.7743 0.03948 0.03246 -0.1245 0.3323 1.0000
13.000 1.7757 0.04133 0.03441 -0.1226 0.3246 1.0000
13.250 1.7894 0.04239 0.03537 -0.1216 0.3175 1.0000
13.500 1.7871 0.04463 0.03777 -0.1197 0.3101 1.0000
13.750 1.7983 0.04590 0.03896 -0.1186 0.3031 1.0000
14.000 1.7986 0.04810 0.04129 -0.1170 0.2961 1.0000
14.250 1.8029 0.04998 0.04319 -0.1158 0.2891 1.0000
14.500 1.8102 0.05169 0.04490 -0.1147 0.2825 1.0000
14.750 1.8089 0.05420 0.04753 -0.1134 0.2756 1.0000
15.000 1.8227 0.05532 0.04853 -0.1127 0.2690 1.0000
15.250 1.8160 0.05848 0.05190 -0.1113 0.2626 1.0000
15.500 1.8195 0.06065 0.05408 -0.1104 0.2562 1.0000
15.750 1.8231 0.06290 0.05637 -0.1096 0.2499 1.0000
16.000 1.8202 0.06590 0.05949 -0.1088 0.2435 1.0000
16.250 1.8315 0.06730 0.06079 -0.1082 0.2373 1.0000
16.500 1.8229 0.07110 0.06480 -0.1075 0.2313 1.0000
16.750 1.8243 0.07372 0.06744 -0.1070 0.2253 1.0000
17.000 1.8263 0.07633 0.07010 -0.1066 0.2195 1.0000
17.250 1.8215 0.07988 0.07377 -0.1063 0.2135 1.0000
17.500 1.8312 0.08148 0.07526 -0.1060 0.2077 1.0000
17.750 1.8212 0.08585 0.07986 -0.1060 0.2022 1.0000
18.000 1.8204 0.08896 0.08302 -0.1059 0.1966 1.0000
18.250 1.8231 0.09157 0.08563 -0.1059 0.1913 1.0000
18.500 1.8162 0.09568 0.08989 -0.1062 0.1858 1.0000
18.750 1.8208 0.09802 0.09219 -0.1063 0.1807 1.0000
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