MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: MH 113 14.62% (mh113-il) Reynolds number: 200,000 Max Cl/Cd: 84.65 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh113-il-200000.txt Download as CSV file: xf-mh113-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.0464 0.10377 0.10005 -0.1113 0.9408 0.0507
-9.500 0.0591 0.10043 0.09670 -0.1149 0.9365 0.0529
-9.250 0.0585 0.09576 0.09205 -0.1266 0.9326 0.0546
-9.000 0.0903 0.09186 0.08813 -0.1265 0.9321 0.0553
-8.750 0.1190 0.08845 0.08469 -0.1296 0.9311 0.0568
-8.500 0.1295 0.08603 0.08228 -0.1307 0.9241 0.0585
-8.250 0.1363 0.08195 0.07819 -0.1392 0.9182 0.0621
-8.000 0.1541 0.07701 0.07325 -0.1451 0.9154 0.0632
-7.750 0.1700 0.07513 0.07137 -0.1437 0.9092 0.0642
-7.500 0.1879 0.07273 0.06895 -0.1451 0.9038 0.0659
-7.250 0.2056 0.06922 0.06542 -0.1500 0.8993 0.0694
-6.750 0.1986 0.06270 0.05891 -0.1552 0.8816 0.0732
-6.500 0.1988 0.06182 0.05806 -0.1515 0.8721 0.0742
-6.250 0.2160 0.05933 0.05555 -0.1536 0.8671 0.0764
-5.750 0.1997 0.03386 0.02889 -0.1816 0.8473 0.0487
-5.500 0.2050 0.03093 0.02555 -0.1802 0.8375 0.0459
-5.250 0.2374 0.02759 0.02168 -0.1831 0.8339 0.0455
-5.000 0.2741 0.02470 0.01826 -0.1858 0.8312 0.0445
-4.750 0.2934 0.02335 0.01662 -0.1847 0.8241 0.0444
-4.500 0.3231 0.02200 0.01497 -0.1852 0.8192 0.0449
-4.250 0.3584 0.02072 0.01342 -0.1865 0.8159 0.0462
-4.000 0.3954 0.01954 0.01207 -0.1881 0.8132 0.0482
-3.750 0.4118 0.01929 0.01189 -0.1861 0.8051 0.0510
-3.500 0.4436 0.01855 0.01105 -0.1868 0.8006 0.0554
-3.250 0.4792 0.01777 0.01026 -0.1881 0.7973 0.0613
-3.000 0.5038 0.01732 0.00985 -0.1876 0.7910 0.0706
-2.750 0.5327 0.01671 0.00935 -0.1879 0.7853 0.0967
-2.500 0.5676 0.01607 0.00885 -0.1894 0.7813 0.1426
-2.250 0.5987 0.01575 0.00865 -0.1901 0.7765 0.1933
-2.000 0.6228 0.01561 0.00867 -0.1895 0.7694 0.2456
-1.750 0.6556 0.01527 0.00845 -0.1905 0.7648 0.3048
-1.500 0.6890 0.01503 0.00829 -0.1915 0.7605 0.3633
-1.250 0.7108 0.01503 0.00842 -0.1903 0.7528 0.4127
-1.000 0.7423 0.01483 0.00829 -0.1909 0.7478 0.4683
-0.750 0.7733 0.01469 0.00823 -0.1912 0.7428 0.5211
-0.500 0.7954 0.01472 0.00837 -0.1900 0.7353 0.5661
-0.250 0.8263 0.01456 0.00825 -0.1903 0.7301 0.6148
0.000 0.8522 0.01453 0.00829 -0.1896 0.7240 0.6586
0.250 0.8751 0.01450 0.00835 -0.1884 0.7169 0.7017
0.500 0.9044 0.01432 0.00819 -0.1882 0.7118 0.7486
0.750 0.9223 0.01434 0.00832 -0.1859 0.7044 0.7960
1.000 0.9409 0.01416 0.00822 -0.1834 0.6979 0.8544
1.250 0.9664 0.01384 0.00790 -0.1823 0.6925 1.0000
1.500 0.9914 0.01401 0.00801 -0.1820 0.6840 1.0000
1.750 1.0254 0.01402 0.00784 -0.1832 0.6781 1.0000
2.000 1.0497 0.01420 0.00797 -0.1826 0.6700 1.0000
2.250 1.0796 0.01425 0.00791 -0.1830 0.6630 1.0000
2.500 1.1066 0.01439 0.00797 -0.1829 0.6556 1.0000
2.750 1.1329 0.01450 0.00801 -0.1826 0.6476 1.0000
3.000 1.1619 0.01462 0.00802 -0.1828 0.6406 1.0000
3.250 1.1853 0.01478 0.00816 -0.1820 0.6318 1.0000
3.500 1.2152 0.01489 0.00815 -0.1824 0.6248 1.0000
3.750 1.2365 0.01509 0.00836 -0.1812 0.6155 1.0000
4.000 1.2659 0.01522 0.00837 -0.1815 0.6082 1.0000
4.250 1.2862 0.01545 0.00861 -0.1801 0.5987 1.0000
4.500 1.3140 0.01562 0.00868 -0.1801 0.5908 1.0000
4.750 1.3343 0.01586 0.00893 -0.1788 0.5813 1.0000
5.000 1.3603 0.01607 0.00906 -0.1785 0.5731 1.0000
5.250 1.3807 0.01632 0.00930 -0.1771 0.5635 1.0000
5.500 1.4044 0.01659 0.00953 -0.1765 0.5549 1.0000
5.750 1.4255 0.01684 0.00976 -0.1753 0.5455 1.0000
6.000 1.4463 0.01716 0.01005 -0.1741 0.5363 1.0000
6.250 1.4687 0.01743 0.01027 -0.1732 0.5274 1.0000
6.500 1.4859 0.01779 0.01065 -0.1714 0.5177 1.0000
6.750 1.5101 0.01810 0.01085 -0.1709 0.5091 1.0000
7.000 1.5222 0.01848 0.01129 -0.1681 0.4993 1.0000
7.250 1.5449 0.01883 0.01156 -0.1673 0.4907 1.0000
7.500 1.5548 0.01925 0.01205 -0.1643 0.4812 1.0000
7.750 1.5743 0.01966 0.01240 -0.1630 0.4725 1.0000
8.000 1.5859 0.02013 0.01291 -0.1603 0.4633 1.0000
8.250 1.6027 0.02061 0.01335 -0.1586 0.4545 1.0000
8.500 1.6152 0.02112 0.01389 -0.1563 0.4455 1.0000
8.750 1.6297 0.02168 0.01444 -0.1543 0.4368 1.0000
9.000 1.6425 0.02225 0.01501 -0.1521 0.4280 1.0000
9.250 1.6549 0.02289 0.01568 -0.1499 0.4194 1.0000
9.500 1.6678 0.02352 0.01630 -0.1478 0.4108 1.0000
9.750 1.6783 0.02426 0.01708 -0.1455 0.4023 1.0000
10.000 1.6908 0.02497 0.01778 -0.1435 0.3939 1.0000
10.250 1.6999 0.02582 0.01868 -0.1412 0.3854 1.0000
10.500 1.7116 0.02661 0.01946 -0.1392 0.3772 1.0000
10.750 1.7194 0.02758 0.02050 -0.1368 0.3688 1.0000
11.000 1.7301 0.02848 0.02139 -0.1349 0.3607 1.0000
11.250 1.7370 0.02958 0.02256 -0.1326 0.3525 1.0000
11.500 1.7463 0.03060 0.02357 -0.1306 0.3443 1.0000
11.750 1.7522 0.03183 0.02488 -0.1284 0.3362 1.0000
12.000 1.7601 0.03300 0.02605 -0.1265 0.3282 1.0000
12.250 1.7653 0.03438 0.02751 -0.1244 0.3201 1.0000
12.500 1.7719 0.03570 0.02884 -0.1225 0.3122 1.0000
12.750 1.7761 0.03725 0.03047 -0.1206 0.3042 1.0000
13.000 1.7812 0.03876 0.03200 -0.1188 0.2963 1.0000
13.250 1.7846 0.04047 0.03379 -0.1169 0.2884 1.0000
13.500 1.7882 0.04221 0.03555 -0.1152 0.2805 1.0000
13.750 1.7909 0.04412 0.03754 -0.1136 0.2727 1.0000
14.000 1.7937 0.04605 0.03949 -0.1121 0.2649 1.0000
14.250 1.7955 0.04818 0.04171 -0.1107 0.2573 1.0000
14.500 1.7972 0.05035 0.04391 -0.1093 0.2497 1.0000
14.750 1.7983 0.05268 0.04631 -0.1081 0.2421 1.0000
15.000 1.7987 0.05512 0.04880 -0.1069 0.2346 1.0000
15.250 1.7991 0.05766 0.05140 -0.1059 0.2273 1.0000
15.500 1.7981 0.06040 0.05419 -0.1050 0.2199 1.0000
15.750 1.7984 0.06308 0.05693 -0.1042 0.2128 1.0000
16.000 1.7961 0.06615 0.06008 -0.1035 0.2057 1.0000
16.250 1.7963 0.06897 0.06292 -0.1030 0.1990 1.0000
16.500 1.7926 0.07236 0.06643 -0.1026 0.1921 1.0000
16.750 1.7931 0.07521 0.06924 -0.1022 0.1857 1.0000
17.000 1.7879 0.07898 0.07319 -0.1021 0.1791 1.0000
17.250 1.7896 0.08171 0.07581 -0.1018 0.1728 1.0000
17.500 1.7826 0.08590 0.08024 -0.1020 0.1668 1.0000
17.750 1.7802 0.08936 0.08370 -0.1022 0.1609 1.0000
18.000 1.7768 0.09307 0.08750 -0.1025 0.1552 1.0000
18.250 1.7720 0.09703 0.09156 -0.1030 0.1496 1.0000
18.500 1.7723 0.10012 0.09461 -0.1033 0.1442 1.0000
18.750 1.7652 0.10460 0.09927 -0.1042 0.1390 1.0000
19.000 1.7639 0.10801 0.10267 -0.1048 0.1340 1.0000
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Polar data table (+)
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