MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 112 Airfoil (mh112-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.7 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh112-il-1000000.txt Download as CSV file: xf-mh112-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.2272 0.08713 0.08444 -0.1645 0.8418 0.0171
-10.750 0.2377 0.08562 0.08290 -0.1647 0.8347 0.0173
-10.500 0.1201 0.06060 0.05780 -0.1719 0.8245 0.0143
-10.250 -0.0059 0.03933 0.03621 -0.1836 0.8108 0.0137
-10.000 -0.0448 0.03180 0.02846 -0.1888 0.8005 0.0135
-9.750 -0.0669 0.02722 0.02373 -0.1931 0.7924 0.0134
-9.500 -0.0667 0.02445 0.02068 -0.1953 0.7857 0.0134
-9.250 -0.0581 0.02227 0.01826 -0.1961 0.7801 0.0134
-9.000 -0.0425 0.02066 0.01647 -0.1965 0.7754 0.0134
-8.750 -0.0241 0.01922 0.01483 -0.1968 0.7705 0.0134
-8.500 -0.0032 0.01809 0.01350 -0.1969 0.7655 0.0134
-8.250 0.0197 0.01708 0.01235 -0.1971 0.7612 0.0134
-8.000 0.0437 0.01615 0.01129 -0.1972 0.7571 0.0134
-7.750 0.0684 0.01533 0.01035 -0.1973 0.7526 0.0135
-7.500 0.0938 0.01468 0.00957 -0.1974 0.7480 0.0135
-7.250 0.1200 0.01409 0.00887 -0.1975 0.7435 0.0136
-7.000 0.1467 0.01355 0.00826 -0.1976 0.7397 0.0137
-6.750 0.1740 0.01317 0.00782 -0.1977 0.7354 0.0139
-6.500 0.2010 0.01273 0.00729 -0.1977 0.7311 0.0140
-6.250 0.2283 0.01239 0.00685 -0.1978 0.7263 0.0140
-6.000 0.2555 0.01170 0.00610 -0.1980 0.7224 0.0142
-5.750 0.2834 0.01114 0.00549 -0.1983 0.7183 0.0144
-5.500 0.3114 0.01075 0.00505 -0.1985 0.7140 0.0147
-5.250 0.3393 0.01047 0.00471 -0.1986 0.7093 0.0150
-5.000 0.3677 0.01023 0.00442 -0.1987 0.7050 0.0154
-4.750 0.3963 0.00998 0.00415 -0.1989 0.7008 0.0160
-4.500 0.4248 0.00977 0.00390 -0.1990 0.6963 0.0167
-4.250 0.4531 0.00952 0.00359 -0.1991 0.6917 0.0178
-4.000 0.4815 0.00937 0.00340 -0.1992 0.6870 0.0193
-3.750 0.5103 0.00916 0.00320 -0.1994 0.6827 0.0217
-3.500 0.5388 0.00898 0.00301 -0.1995 0.6779 0.0261
-3.250 0.5670 0.00883 0.00286 -0.1995 0.6730 0.0352
-3.000 0.5953 0.00870 0.00276 -0.1996 0.6683 0.0486
-2.750 0.6240 0.00856 0.00267 -0.1998 0.6636 0.0619
-2.500 0.6521 0.00847 0.00260 -0.1998 0.6584 0.0762
-2.250 0.6797 0.00841 0.00255 -0.1998 0.6532 0.0932
-2.000 0.7082 0.00830 0.00252 -0.2000 0.6486 0.1154
-1.750 0.7366 0.00819 0.00249 -0.2001 0.6433 0.1427
-1.500 0.7642 0.00812 0.00248 -0.2001 0.6378 0.1739
-1.250 0.7917 0.00806 0.00248 -0.2001 0.6324 0.2078
-0.750 0.8472 0.00795 0.00250 -0.2001 0.6206 0.2739
-0.500 0.8737 0.00797 0.00254 -0.1998 0.6141 0.3038
-0.250 0.9014 0.00792 0.00257 -0.1998 0.6077 0.3370
0.000 0.9277 0.00795 0.00261 -0.1995 0.6009 0.3691
0.250 0.9545 0.00796 0.00268 -0.1993 0.5951 0.4044
0.500 0.9817 0.00797 0.00274 -0.1992 0.5892 0.4365
0.750 1.0074 0.00802 0.00282 -0.1988 0.5828 0.4674
1.000 1.0336 0.00807 0.00290 -0.1985 0.5770 0.4964
1.250 1.0602 0.00811 0.00298 -0.1982 0.5712 0.5230
1.500 1.0851 0.00821 0.00307 -0.1977 0.5648 0.5471
1.750 1.1105 0.00828 0.00318 -0.1972 0.5590 0.5714
2.000 1.1364 0.00834 0.00327 -0.1968 0.5531 0.5947
2.250 1.1603 0.00844 0.00339 -0.1961 0.5467 0.6182
2.500 1.1844 0.00853 0.00350 -0.1953 0.5408 0.6440
3.000 1.2296 0.00870 0.00375 -0.1933 0.5284 0.7000
3.250 1.2522 0.00878 0.00390 -0.1923 0.5225 0.7358
3.500 1.2745 0.00884 0.00406 -0.1912 0.5163 0.7828
3.750 1.2920 0.00892 0.00426 -0.1891 0.5099 0.8538
4.000 1.3086 0.00886 0.00435 -0.1868 0.5044 1.0000
4.250 1.3311 0.00903 0.00450 -0.1858 0.4978 1.0000
4.500 1.3506 0.00929 0.00470 -0.1843 0.4909 1.0000
4.750 1.3740 0.00945 0.00485 -0.1836 0.4850 1.0000
5.000 1.3950 0.00968 0.00504 -0.1824 0.4779 1.0000
5.250 1.4142 0.00995 0.00527 -0.1810 0.4712 1.0000
5.500 1.4363 0.01015 0.00546 -0.1800 0.4646 1.0000
5.750 1.4546 0.01046 0.00573 -0.1784 0.4570 1.0000
6.000 1.4749 0.01072 0.00597 -0.1772 0.4501 1.0000
6.250 1.4939 0.01103 0.00625 -0.1758 0.4424 1.0000
6.500 1.5117 0.01138 0.00657 -0.1742 0.4351 1.0000
6.750 1.5307 0.01169 0.00687 -0.1729 0.4272 1.0000
7.000 1.5465 0.01214 0.00727 -0.1710 0.4186 1.0000
7.250 1.5648 0.01250 0.00762 -0.1696 0.4102 1.0000
7.500 1.5794 0.01301 0.00809 -0.1676 0.4013 1.0000
7.750 1.5965 0.01345 0.00850 -0.1661 0.3924 1.0000
8.000 1.6103 0.01403 0.00905 -0.1641 0.3829 1.0000
8.250 1.6250 0.01459 0.00958 -0.1623 0.3731 1.0000
8.500 1.6387 0.01522 0.01018 -0.1605 0.3638 1.0000
8.750 1.6506 0.01596 0.01087 -0.1584 0.3535 1.0000
9.000 1.6649 0.01661 0.01151 -0.1567 0.3447 1.0000
9.250 1.6749 0.01749 0.01234 -0.1544 0.3347 1.0000
9.500 1.6891 0.01819 0.01304 -0.1528 0.3265 1.0000
9.750 1.6990 0.01914 0.01395 -0.1507 0.3177 1.0000
10.000 1.7124 0.01993 0.01474 -0.1491 0.3101 1.0000
10.250 1.7213 0.02100 0.01577 -0.1471 0.3016 1.0000
10.500 1.7352 0.02181 0.01659 -0.1457 0.2953 1.0000
10.750 1.7441 0.02294 0.01770 -0.1437 0.2871 1.0000
11.000 1.7566 0.02388 0.01865 -0.1423 0.2815 1.0000
11.250 1.7675 0.02494 0.01971 -0.1407 0.2745 1.0000
11.500 1.7758 0.02622 0.02097 -0.1389 0.2681 1.0000
11.750 1.7888 0.02720 0.02197 -0.1376 0.2623 1.0000
12.000 1.7962 0.02861 0.02337 -0.1359 0.2556 1.0000
12.250 1.8073 0.02977 0.02455 -0.1346 0.2501 1.0000
12.500 1.8171 0.03106 0.02585 -0.1332 0.2440 1.0000
12.750 1.8229 0.03269 0.02746 -0.1316 0.2373 1.0000
13.000 1.8348 0.03388 0.02869 -0.1305 0.2323 1.0000
13.250 1.8411 0.03556 0.03036 -0.1291 0.2258 1.0000
13.500 1.8491 0.03711 0.03193 -0.1278 0.2201 1.0000
13.750 1.8571 0.03872 0.03355 -0.1266 0.2142 1.0000
14.000 1.8606 0.04075 0.03557 -0.1252 0.2076 1.0000
14.250 1.8698 0.04231 0.03717 -0.1242 0.2024 1.0000
14.500 1.8744 0.04433 0.03918 -0.1230 0.1962 1.0000
14.750 1.8796 0.04633 0.04120 -0.1220 0.1907 1.0000
15.000 1.8859 0.04825 0.04314 -0.1210 0.1852 1.0000
15.250 1.8866 0.05079 0.04568 -0.1199 0.1792 1.0000
15.500 1.8944 0.05264 0.04757 -0.1192 0.1745 1.0000
15.750 1.8958 0.05520 0.05015 -0.1183 0.1689 1.0000
16.000 1.8993 0.05756 0.05254 -0.1175 0.1640 1.0000
16.250 1.9030 0.05996 0.05496 -0.1169 0.1591 1.0000
16.500 1.9017 0.06295 0.05796 -0.1162 0.1536 1.0000
16.750 1.9066 0.06529 0.06035 -0.1157 0.1494 1.0000
17.000 1.9071 0.06817 0.06326 -0.1152 0.1446 1.0000
17.250 1.9069 0.07118 0.06629 -0.1148 0.1400 1.0000
17.500 1.9094 0.07390 0.06906 -0.1145 0.1360 1.0000
17.750 1.9083 0.07710 0.07228 -0.1143 0.1313 1.0000
18.000 1.9074 0.08035 0.07557 -0.1141 0.1274 1.0000
18.250 1.9093 0.08322 0.07849 -0.1141 0.1233 1.0000
18.500 1.9047 0.08702 0.08231 -0.1141 0.1192 1.0000
18.750 1.9054 0.09012 0.08546 -0.1142 0.1156 1.0000
19.000 1.9041 0.09354 0.08893 -0.1144 0.1120 1.0000
19.250 1.8986 0.09757 0.09298 -0.1148 0.1080 1.0000
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