MH 112 Airfoil (mh112-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 112 Airfoil (mh112-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.59 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh112-il-1000000-n5.txt Download as CSV file: xf-mh112-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.0268 0.07373 0.07063 -0.1627 0.8354 0.0091
-12.750 -0.0742 0.06331 0.06004 -0.1679 0.8259 0.0090
-12.500 -0.0988 0.05703 0.05363 -0.1711 0.8177 0.0089
-12.000 -0.1510 0.04496 0.04132 -0.1772 0.8004 0.0089
-11.750 -0.1900 0.03759 0.03382 -0.1811 0.7920 0.0088
-11.500 -0.2073 0.03286 0.02896 -0.1835 0.7839 0.0088
-11.250 -0.2395 0.02702 0.02295 -0.1868 0.7763 0.0088
-11.000 -0.2408 0.02327 0.01900 -0.1920 0.7689 0.0088
-10.500 -0.2131 0.02042 0.01587 -0.1934 0.7588 0.0088
-10.250 -0.1936 0.01944 0.01477 -0.1937 0.7540 0.0089
-10.000 -0.1743 0.01836 0.01356 -0.1939 0.7490 0.0089
-9.750 -0.1536 0.01739 0.01244 -0.1941 0.7441 0.0089
-9.500 -0.1306 0.01648 0.01143 -0.1944 0.7404 0.0090
-9.250 -0.1066 0.01570 0.01055 -0.1946 0.7359 0.0091
-9.000 -0.0820 0.01505 0.00980 -0.1947 0.7312 0.0092
-8.750 -0.0568 0.01449 0.00914 -0.1948 0.7267 0.0093
-8.500 -0.0304 0.01399 0.00858 -0.1950 0.7228 0.0094
-8.250 -0.0036 0.01355 0.00808 -0.1952 0.7185 0.0095
-8.000 0.0233 0.01314 0.00761 -0.1953 0.7141 0.0096
-7.750 0.0501 0.01278 0.00717 -0.1953 0.7094 0.0097
-7.500 0.0773 0.01242 0.00675 -0.1954 0.7053 0.0098
-7.250 0.1052 0.01206 0.00634 -0.1956 0.7013 0.0099
-7.000 0.1329 0.01175 0.00597 -0.1958 0.6965 0.0100
-6.750 0.1604 0.01147 0.00563 -0.1958 0.6918 0.0101
-6.500 0.1881 0.01121 0.00531 -0.1959 0.6876 0.0103
-6.250 0.2166 0.01094 0.00500 -0.1961 0.6836 0.0105
-6.000 0.2448 0.01071 0.00472 -0.1962 0.6787 0.0106
-5.750 0.2726 0.01050 0.00446 -0.1962 0.6738 0.0109
-5.500 0.3005 0.01032 0.00422 -0.1962 0.6694 0.0111
-5.250 0.3292 0.01014 0.00401 -0.1964 0.6654 0.0113
-5.000 0.3576 0.00993 0.00377 -0.1965 0.6604 0.0117
-4.750 0.3855 0.00978 0.00357 -0.1965 0.6550 0.0123
-4.500 0.4135 0.00965 0.00341 -0.1965 0.6506 0.0130
-4.250 0.4422 0.00952 0.00326 -0.1967 0.6463 0.0137
-4.000 0.4705 0.00940 0.00312 -0.1967 0.6411 0.0147
-3.750 0.4981 0.00932 0.00300 -0.1966 0.6356 0.0161
-3.500 0.5263 0.00922 0.00288 -0.1967 0.6309 0.0181
-3.250 0.5548 0.00912 0.00279 -0.1968 0.6260 0.0208
-3.000 0.5827 0.00904 0.00270 -0.1967 0.6206 0.0254
-2.750 0.6099 0.00899 0.00263 -0.1966 0.6151 0.0314
-2.500 0.6384 0.00891 0.00257 -0.1967 0.6101 0.0394
-2.250 0.6663 0.00884 0.00252 -0.1967 0.6047 0.0486
-2.000 0.6934 0.00880 0.00248 -0.1966 0.5991 0.0609
-1.750 0.7214 0.00873 0.00245 -0.1966 0.5940 0.0779
-1.500 0.7493 0.00865 0.00244 -0.1967 0.5883 0.0996
-1.250 0.7763 0.00861 0.00244 -0.1966 0.5824 0.1246
-1.000 0.8036 0.00857 0.00245 -0.1965 0.5768 0.1495
-0.750 0.8308 0.00854 0.00246 -0.1964 0.5698 0.1744
-0.250 0.8833 0.00859 0.00254 -0.1958 0.5544 0.2191
0.000 0.9088 0.00864 0.00260 -0.1954 0.5463 0.2426
0.250 0.9352 0.00865 0.00266 -0.1951 0.5401 0.2719
0.500 0.9615 0.00868 0.00272 -0.1948 0.5336 0.2992
0.750 0.9863 0.00875 0.00280 -0.1943 0.5268 0.3250
1.000 1.0125 0.00878 0.00288 -0.1940 0.5212 0.3537
1.250 1.0381 0.00883 0.00297 -0.1936 0.5149 0.3823
1.500 1.0612 0.00893 0.00308 -0.1927 0.5084 0.4084
1.750 1.0859 0.00898 0.00317 -0.1921 0.5029 0.4354
2.000 1.1094 0.00906 0.00328 -0.1913 0.4965 0.4604
2.250 1.1311 0.00918 0.00341 -0.1901 0.4903 0.4827
2.500 1.1552 0.00926 0.00354 -0.1894 0.4846 0.5082
2.750 1.1779 0.00940 0.00368 -0.1885 0.4779 0.5295
3.000 1.1996 0.00956 0.00385 -0.1873 0.4717 0.5497
3.250 1.2233 0.00968 0.00400 -0.1866 0.4656 0.5719
3.500 1.2445 0.00986 0.00420 -0.1854 0.4582 0.5929
3.750 1.2662 0.01003 0.00438 -0.1843 0.4523 0.6146
4.000 1.2887 0.01018 0.00457 -0.1834 0.4457 0.6386
4.250 1.3082 0.01041 0.00482 -0.1819 0.4379 0.6653
4.500 1.3301 0.01057 0.00503 -0.1809 0.4315 0.6949
5.000 1.3693 0.01096 0.00557 -0.1782 0.4162 0.7839
5.250 1.3812 0.01096 0.00585 -0.1751 0.4085 0.9275
5.500 1.4005 0.01125 0.00612 -0.1737 0.4006 1.0000
5.750 1.4194 0.01159 0.00642 -0.1723 0.3913 1.0000
6.000 1.4363 0.01200 0.00678 -0.1706 0.3820 1.0000
6.250 1.4538 0.01241 0.00715 -0.1691 0.3725 1.0000
6.500 1.4704 0.01285 0.00755 -0.1674 0.3638 1.0000
6.750 1.4864 0.01334 0.00799 -0.1657 0.3541 1.0000
7.000 1.5018 0.01387 0.00847 -0.1639 0.3441 1.0000
7.250 1.5159 0.01447 0.00903 -0.1620 0.3345 1.0000
7.500 1.5318 0.01501 0.00954 -0.1604 0.3258 1.0000
7.750 1.5454 0.01567 0.01015 -0.1585 0.3172 1.0000
8.000 1.5607 0.01627 0.01073 -0.1569 0.3089 1.0000
8.250 1.5735 0.01701 0.01144 -0.1550 0.3009 1.0000
8.500 1.5893 0.01762 0.01204 -0.1535 0.2941 1.0000
8.750 1.6014 0.01844 0.01283 -0.1516 0.2866 1.0000
9.000 1.6168 0.01911 0.01349 -0.1503 0.2806 1.0000
9.250 1.6293 0.01995 0.01432 -0.1485 0.2734 1.0000
9.500 1.6423 0.02079 0.01514 -0.1469 0.2672 1.0000
9.750 1.6564 0.02158 0.01594 -0.1455 0.2616 1.0000
10.000 1.6679 0.02256 0.01690 -0.1438 0.2553 1.0000
10.250 1.6810 0.02346 0.01780 -0.1424 0.2496 1.0000
10.500 1.6934 0.02443 0.01877 -0.1410 0.2438 1.0000
10.750 1.7031 0.02559 0.01992 -0.1393 0.2369 1.0000
11.000 1.7162 0.02656 0.02091 -0.1380 0.2324 1.0000
11.250 1.7262 0.02777 0.02210 -0.1365 0.2253 1.0000
11.500 1.7365 0.02900 0.02333 -0.1350 0.2204 1.0000
11.750 1.7479 0.03016 0.02450 -0.1338 0.2145 1.0000
12.000 1.7549 0.03168 0.02601 -0.1322 0.2081 1.0000
12.250 1.7663 0.03290 0.02725 -0.1310 0.2032 1.0000
12.500 1.7746 0.03441 0.02875 -0.1297 0.1972 1.0000
12.750 1.7823 0.03599 0.03034 -0.1283 0.1913 1.0000
13.000 1.7909 0.03752 0.03188 -0.1271 0.1856 1.0000
13.250 1.7963 0.03937 0.03373 -0.1258 0.1796 1.0000
13.500 1.8057 0.04091 0.03530 -0.1248 0.1752 1.0000
13.750 1.8114 0.04282 0.03721 -0.1236 0.1692 1.0000
14.000 1.8174 0.04473 0.03913 -0.1225 0.1641 1.0000
14.250 1.8237 0.04665 0.04107 -0.1215 0.1587 1.0000
14.500 1.8266 0.04895 0.04337 -0.1204 0.1529 1.0000
14.750 1.8335 0.05090 0.04534 -0.1196 0.1486 1.0000
15.000 1.8375 0.05316 0.04762 -0.1188 0.1436 1.0000
15.250 1.8414 0.05549 0.04997 -0.1180 0.1392 1.0000
15.500 1.8465 0.05772 0.05223 -0.1173 0.1348 1.0000
15.750 1.8483 0.06036 0.05489 -0.1166 0.1301 1.0000
16.000 1.8528 0.06274 0.05731 -0.1160 0.1267 1.0000
16.250 1.8561 0.06529 0.05989 -0.1156 0.1224 1.0000
16.500 1.8562 0.06826 0.06288 -0.1151 0.1182 1.0000
16.750 1.8602 0.07079 0.06546 -0.1147 0.1147 1.0000
17.000 1.8612 0.07373 0.06843 -0.1144 0.1108 1.0000
17.500 1.8635 0.07970 0.07448 -0.1141 0.1042 1.0000
17.750 1.8646 0.08274 0.07755 -0.1140 0.1005 1.0000
18.000 1.8621 0.08629 0.08114 -0.1141 0.0972 1.0000
18.250 1.8645 0.08917 0.08408 -0.1142 0.0942 1.0000
18.500 1.8628 0.09271 0.08766 -0.1144 0.0911 1.0000
18.750 1.8608 0.09627 0.09126 -0.1147 0.0879 1.0000
19.000 1.8611 0.09956 0.09461 -0.1150 0.0855 1.0000
19.250 1.8597 0.10307 0.09816 -0.1155 0.0824 1.0000
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