MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 113 14.62% (mh113-il) Reynolds number: 1,000,000 Max Cl/Cd: 152.95 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh113-il-1000000.txt Download as CSV file: xf-mh113-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.1639 0.08598 0.08381 -0.1508 0.9126 0.0172
-10.250 0.1810 0.08288 0.08062 -0.1546 0.9000 0.0176
-10.000 0.2010 0.06516 0.06275 -0.1478 0.8424 0.0197
-9.750 0.2095 0.06331 0.06088 -0.1479 0.8351 0.0199
-9.500 0.2154 0.06089 0.05842 -0.1482 0.8282 0.0201
-9.250 0.0863 0.05017 0.04766 -0.1682 0.8430 0.0166
-9.000 -0.0059 0.03347 0.03073 -0.1784 0.8244 0.0152
-8.750 -0.0473 0.02252 0.01891 -0.1896 0.8111 0.0145
-8.500 -0.0302 0.02077 0.01694 -0.1902 0.8054 0.0146
-8.250 -0.0122 0.01874 0.01459 -0.1907 0.7997 0.0147
-8.000 0.0093 0.01714 0.01272 -0.1911 0.7944 0.0147
-7.750 0.0332 0.01599 0.01140 -0.1913 0.7896 0.0148
-7.500 0.0582 0.01507 0.01032 -0.1914 0.7845 0.0150
-7.250 0.0840 0.01432 0.00939 -0.1915 0.7794 0.0152
-7.000 0.1105 0.01363 0.00859 -0.1916 0.7750 0.0155
-6.750 0.1374 0.01306 0.00793 -0.1917 0.7702 0.0157
-6.500 0.1645 0.01261 0.00737 -0.1918 0.7653 0.0160
-6.250 0.1920 0.01224 0.00689 -0.1919 0.7605 0.0162
-6.000 0.2192 0.01154 0.00612 -0.1920 0.7560 0.0164
-5.750 0.2466 0.01094 0.00546 -0.1922 0.7511 0.0168
-5.500 0.2744 0.01058 0.00504 -0.1924 0.7461 0.0172
-5.250 0.3026 0.01028 0.00470 -0.1925 0.7416 0.0176
-5.000 0.3309 0.00998 0.00438 -0.1927 0.7367 0.0180
-4.750 0.3591 0.00975 0.00408 -0.1928 0.7316 0.0185
-4.500 0.3874 0.00956 0.00382 -0.1929 0.7266 0.0191
-4.250 0.4161 0.00927 0.00351 -0.1931 0.7219 0.0198
-4.000 0.4445 0.00904 0.00325 -0.1932 0.7166 0.0210
-3.750 0.4726 0.00891 0.00306 -0.1933 0.7113 0.0221
-3.500 0.5013 0.00874 0.00287 -0.1934 0.7064 0.0233
-3.250 0.5299 0.00856 0.00268 -0.1935 0.7009 0.0253
-3.000 0.5580 0.00844 0.00252 -0.1935 0.6954 0.0291
-2.750 0.5868 0.00822 0.00237 -0.1938 0.6902 0.0465
-2.500 0.6154 0.00805 0.00227 -0.1940 0.6844 0.0712
-2.250 0.6433 0.00796 0.00221 -0.1940 0.6785 0.0938
-2.000 0.6717 0.00784 0.00217 -0.1942 0.6731 0.1191
-1.750 0.7000 0.00775 0.00213 -0.1943 0.6669 0.1464
-1.500 0.7275 0.00770 0.00212 -0.1942 0.6606 0.1761
-1.250 0.7560 0.00759 0.00211 -0.1944 0.6547 0.2151
-1.000 0.7839 0.00752 0.00212 -0.1945 0.6480 0.2582
-0.750 0.8113 0.00748 0.00214 -0.1944 0.6416 0.2993
-0.500 0.8394 0.00742 0.00217 -0.1946 0.6348 0.3420
-0.250 0.8664 0.00742 0.00221 -0.1944 0.6277 0.3785
0.000 0.8941 0.00740 0.00225 -0.1944 0.6210 0.4164
0.250 0.9212 0.00741 0.00231 -0.1943 0.6134 0.4555
0.500 0.9481 0.00743 0.00238 -0.1941 0.6063 0.4906
0.750 0.9751 0.00746 0.00244 -0.1939 0.5986 0.5254
1.000 1.0012 0.00752 0.00253 -0.1936 0.5911 0.5591
1.250 1.0281 0.00755 0.00261 -0.1934 0.5833 0.5910
1.500 1.0534 0.00764 0.00271 -0.1929 0.5751 0.6228
1.750 1.0801 0.00768 0.00280 -0.1927 0.5673 0.6556
2.000 1.1047 0.00779 0.00293 -0.1921 0.5587 0.6885
2.250 1.1308 0.00783 0.00303 -0.1918 0.5506 0.7240
2.500 1.1545 0.00794 0.00317 -0.1910 0.5418 0.7625
2.750 1.1793 0.00797 0.00330 -0.1903 0.5335 0.8082
3.000 1.1990 0.00803 0.00345 -0.1886 0.5249 0.8732
3.250 1.2175 0.00796 0.00350 -0.1865 0.5167 1.0000
3.500 1.2406 0.00817 0.00364 -0.1857 0.5077 1.0000
3.750 1.2647 0.00832 0.00376 -0.1850 0.4989 1.0000
4.000 1.2860 0.00853 0.00390 -0.1838 0.4900 1.0000
4.250 1.3085 0.00871 0.00405 -0.1828 0.4808 1.0000
4.500 1.3294 0.00893 0.00422 -0.1815 0.4721 1.0000
4.750 1.3506 0.00915 0.00440 -0.1803 0.4626 1.0000
5.000 1.3716 0.00938 0.00459 -0.1791 0.4540 1.0000
5.250 1.3918 0.00964 0.00480 -0.1778 0.4443 1.0000
5.500 1.4127 0.00987 0.00501 -0.1766 0.4357 1.0000
5.750 1.4318 0.01017 0.00525 -0.1750 0.4265 1.0000
6.000 1.4528 0.01042 0.00547 -0.1739 0.4181 1.0000
6.500 1.4912 0.01102 0.00602 -0.1710 0.4005 1.0000
6.750 1.5084 0.01141 0.00635 -0.1693 0.3914 1.0000
7.000 1.5285 0.01169 0.00663 -0.1681 0.3833 1.0000
7.250 1.5448 0.01211 0.00700 -0.1663 0.3748 1.0000
7.500 1.5645 0.01242 0.00731 -0.1650 0.3669 1.0000
7.750 1.5798 0.01290 0.00775 -0.1631 0.3581 1.0000
8.000 1.5987 0.01326 0.00811 -0.1618 0.3505 1.0000
8.250 1.6133 0.01380 0.00860 -0.1598 0.3420 1.0000
8.500 1.6317 0.01419 0.00900 -0.1585 0.3348 1.0000
9.000 1.6629 0.01525 0.01003 -0.1552 0.3189 1.0000
9.500 1.6926 0.01644 0.01119 -0.1517 0.3033 1.0000
9.750 1.7056 0.01716 0.01188 -0.1498 0.2953 1.0000
10.000 1.7208 0.01777 0.01251 -0.1483 0.2880 1.0000
10.250 1.7329 0.01858 0.01329 -0.1464 0.2797 1.0000
10.500 1.7472 0.01929 0.01400 -0.1448 0.2727 1.0000
10.750 1.7584 0.02019 0.01488 -0.1429 0.2643 1.0000
11.000 1.7717 0.02099 0.01569 -0.1414 0.2572 1.0000
11.250 1.7821 0.02200 0.01668 -0.1395 0.2491 1.0000
11.500 1.7945 0.02291 0.01760 -0.1380 0.2421 1.0000
11.750 1.8041 0.02402 0.01870 -0.1361 0.2342 1.0000
12.000 1.8152 0.02506 0.01975 -0.1346 0.2268 1.0000
12.250 1.8234 0.02633 0.02100 -0.1328 0.2189 1.0000
12.500 1.8340 0.02747 0.02216 -0.1313 0.2119 1.0000
12.750 1.8409 0.02892 0.02359 -0.1295 0.2040 1.0000
13.000 1.8502 0.03022 0.02490 -0.1280 0.1968 1.0000
13.250 1.8565 0.03180 0.02647 -0.1264 0.1894 1.0000
13.500 1.8643 0.03330 0.02798 -0.1249 0.1822 1.0000
13.750 1.8691 0.03508 0.02975 -0.1233 0.1744 1.0000
14.000 1.8761 0.03673 0.03142 -0.1220 0.1679 1.0000
14.250 1.8795 0.03874 0.03342 -0.1205 0.1605 1.0000
14.500 1.8855 0.04058 0.03527 -0.1193 0.1535 1.0000
14.750 1.8870 0.04288 0.03756 -0.1179 0.1464 1.0000
15.000 1.8926 0.04483 0.03954 -0.1168 0.1400 1.0000
15.250 1.8930 0.04736 0.04207 -0.1156 0.1332 1.0000
15.500 1.8978 0.04950 0.04425 -0.1147 0.1283 1.0000
15.750 1.8995 0.05203 0.04678 -0.1138 0.1225 1.0000
16.000 1.9016 0.05455 0.04934 -0.1130 0.1178 1.0000
16.250 1.9034 0.05718 0.05200 -0.1122 0.1126 1.0000
16.500 1.9018 0.06025 0.05508 -0.1115 0.1068 1.0000
16.750 1.9035 0.06300 0.05787 -0.1110 0.1023 1.0000
17.000 1.8998 0.06646 0.06136 -0.1106 0.0970 1.0000
17.250 1.9014 0.06933 0.06428 -0.1103 0.0933 1.0000
17.500 1.8995 0.07268 0.06766 -0.1100 0.0890 1.0000
17.750 1.8953 0.07643 0.07145 -0.1099 0.0849 1.0000
18.000 1.8951 0.07970 0.07478 -0.1100 0.0816 1.0000
18.250 1.8906 0.08358 0.07870 -0.1101 0.0776 1.0000
18.500 1.8866 0.08746 0.08263 -0.1104 0.0742 1.0000
18.750 1.8831 0.09132 0.08656 -0.1108 0.0710 1.0000
19.000 1.8766 0.09567 0.09095 -0.1113 0.0677 1.0000
19.250 1.8733 0.09959 0.09493 -0.1119 0.0650 1.0000
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