S1210 12% (s1210-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1210 12% (s1210-il) Reynolds number: 100,000 Max Cl/Cd: 66.01 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1210-il-100000-n5.txt Download as CSV file: xf-s1210-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1210 12%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.0903 0.09671 0.09217 -0.0619 0.9502 0.0644
-6.750 -0.0796 0.09354 0.08901 -0.0647 0.9400 0.0659
-6.250 -0.0710 0.08243 0.07791 -0.0724 0.9169 0.0375
-6.000 -0.0595 0.07910 0.07458 -0.0742 0.9063 0.0360
-5.750 -0.0586 0.06967 0.06516 -0.0839 0.8908 0.0315
-5.250 -0.0272 0.06185 0.05734 -0.0910 0.8660 0.0307
-5.000 0.0007 0.05371 0.04912 -0.1032 0.8560 0.0299
-4.750 0.1657 0.02996 0.02361 -0.1687 0.8550 0.0299
-4.500 0.2353 0.02644 0.01929 -0.1800 0.8476 0.0316
-4.250 0.2874 0.02422 0.01683 -0.1857 0.8398 0.0323
-4.000 0.3357 0.02265 0.01509 -0.1900 0.8294 0.0334
-3.750 0.3837 0.02141 0.01370 -0.1940 0.8174 0.0349
-3.500 0.4355 0.02037 0.01246 -0.1987 0.8045 0.0374
-3.250 0.4946 0.01935 0.01127 -0.2053 0.7902 0.0429
-3.000 0.5582 0.01838 0.01001 -0.2130 0.7741 0.0504
-2.750 0.6331 0.01677 0.00869 -0.2241 0.7573 0.1607
-2.500 0.6727 0.01719 0.00903 -0.2261 0.7387 0.2745
-2.250 0.7060 0.01787 0.00957 -0.2267 0.7209 0.3168
-2.000 0.7409 0.01794 0.00942 -0.2278 0.7045 0.3269
-1.750 0.7775 0.01795 0.00911 -0.2294 0.6892 0.3365
-1.500 0.8099 0.01800 0.00901 -0.2301 0.6756 0.3423
-1.250 0.8434 0.01806 0.00884 -0.2312 0.6633 0.3492
-1.000 0.8755 0.01811 0.00873 -0.2320 0.6517 0.3548
-0.750 0.9066 0.01821 0.00871 -0.2325 0.6416 0.3604
-0.500 0.9381 0.01833 0.00866 -0.2331 0.6317 0.3673
-0.250 0.9684 0.01845 0.00869 -0.2336 0.6222 0.3728
0.000 0.9989 0.01860 0.00873 -0.2340 0.6139 0.3788
0.250 1.0290 0.01876 0.00881 -0.2344 0.6056 0.3867
0.500 1.0587 0.01893 0.00895 -0.2347 0.5985 0.3938
0.750 1.0887 0.01914 0.00907 -0.2351 0.5915 0.4030
1.000 1.1176 0.01933 0.00927 -0.2352 0.5844 0.4106
1.250 1.1478 0.01956 0.00941 -0.2356 0.5785 0.4207
1.500 1.1759 0.01977 0.00969 -0.2356 0.5719 0.4312
1.750 1.2049 0.02001 0.00992 -0.2358 0.5661 0.4435
2.000 1.2337 0.02027 0.01017 -0.2359 0.5608 0.4575
2.250 1.2611 0.02053 0.01049 -0.2358 0.5546 0.4727
2.500 1.2894 0.02080 0.01079 -0.2358 0.5493 0.4895
2.750 1.3178 0.02108 0.01110 -0.2359 0.5444 0.5091
3.000 1.3445 0.02137 0.01150 -0.2356 0.5384 0.5321
3.250 1.3721 0.02165 0.01187 -0.2355 0.5332 0.5584
3.500 1.3996 0.02194 0.01221 -0.2354 0.5281 0.5891
3.750 1.4244 0.02222 0.01266 -0.2347 0.5212 0.6241
4.000 1.4503 0.02246 0.01297 -0.2342 0.5148 0.6674
4.250 1.4729 0.02269 0.01341 -0.2330 0.5081 0.7198
4.500 1.4922 0.02284 0.01374 -0.2310 0.5018 0.7954
4.750 1.5083 0.02285 0.01381 -0.2283 0.4970 1.0000
5.000 1.5331 0.02329 0.01435 -0.2279 0.4900 1.0000
5.250 1.5593 0.02367 0.01472 -0.2275 0.4833 1.0000
5.500 1.5839 0.02408 0.01515 -0.2269 0.4759 1.0000
5.750 1.6078 0.02445 0.01555 -0.2261 0.4676 1.0000
6.000 1.6311 0.02485 0.01601 -0.2253 0.4595 1.0000
6.250 1.6537 0.02523 0.01643 -0.2243 0.4508 1.0000
6.500 1.6755 0.02565 0.01693 -0.2231 0.4419 1.0000
6.750 1.6973 0.02604 0.01735 -0.2219 0.4329 1.0000
7.000 1.7169 0.02651 0.01795 -0.2204 0.4229 1.0000
7.250 1.7374 0.02695 0.01841 -0.2190 0.4136 1.0000
7.500 1.7556 0.02746 0.01907 -0.2173 0.4029 1.0000
7.750 1.7732 0.02799 0.01972 -0.2154 0.3918 1.0000
8.000 1.7899 0.02855 0.02034 -0.2134 0.3805 1.0000
8.250 1.8044 0.02916 0.02104 -0.2111 0.3678 1.0000
8.500 1.8168 0.02986 0.02188 -0.2084 0.3534 1.0000
8.750 1.8262 0.03064 0.02275 -0.2052 0.3385 1.0000
9.000 1.8341 0.03154 0.02369 -0.2019 0.3226 1.0000
9.250 1.8398 0.03262 0.02477 -0.1983 0.3059 1.0000
9.500 1.8438 0.03391 0.02607 -0.1947 0.2888 1.0000
9.750 1.8458 0.03545 0.02759 -0.1911 0.2723 1.0000
10.000 1.8461 0.03723 0.02938 -0.1874 0.2570 1.0000
10.250 1.8451 0.03924 0.03138 -0.1839 0.2433 1.0000
10.500 1.8430 0.04147 0.03363 -0.1805 0.2312 1.0000
10.750 1.8418 0.04378 0.03602 -0.1776 0.2201 1.0000
11.000 1.8393 0.04634 0.03864 -0.1748 0.2107 1.0000
11.250 1.8357 0.04915 0.04150 -0.1723 0.2022 1.0000
11.500 1.8336 0.05199 0.04445 -0.1702 0.1941 1.0000
11.750 1.8293 0.05519 0.04773 -0.1683 0.1870 1.0000
12.000 1.8273 0.05831 0.05097 -0.1668 0.1803 1.0000
12.250 1.8239 0.06171 0.05446 -0.1654 0.1741 1.0000
12.500 1.8210 0.06517 0.05798 -0.1643 0.1686 1.0000
12.750 1.8202 0.06853 0.06149 -0.1635 0.1629 1.0000
13.000 1.8173 0.07217 0.06517 -0.1628 0.1580 1.0000
13.250 1.8175 0.07552 0.06862 -0.1622 0.1536 1.0000
13.500 1.8185 0.07881 0.07208 -0.1617 0.1492 1.0000
13.750 1.8194 0.08213 0.07550 -0.1613 0.1454 1.0000
14.000 1.8223 0.08507 0.07842 -0.1607 0.1421 1.0000
14.250 1.8244 0.08837 0.08194 -0.1605 0.1384 1.0000
14.500 1.8260 0.09172 0.08545 -0.1604 0.1348 1.0000
14.750 1.8280 0.09494 0.08876 -0.1604 0.1314 1.0000
15.000 1.8344 0.09736 0.09117 -0.1599 0.1284 1.0000
15.250 1.8357 0.10087 0.09491 -0.1602 0.1256 1.0000
15.500 1.8367 0.10440 0.09865 -0.1605 0.1226 1.0000
15.750 1.8384 0.10776 0.10218 -0.1609 0.1197 1.0000
16.000 1.8411 0.11087 0.10537 -0.1613 0.1168 1.0000
16.250 1.8470 0.11344 0.10798 -0.1614 0.1140 1.0000
16.500 1.8415 0.11820 0.11303 -0.1629 0.1112 1.0000
16.750 1.8384 0.12250 0.11755 -0.1643 0.1084 1.0000
17.000 1.8377 0.12633 0.12151 -0.1655 0.1056 1.0000
17.250 1.8411 0.12925 0.12447 -0.1663 0.1028 1.0000
17.500 1.8391 0.13336 0.12875 -0.1679 0.1003 1.0000
17.750 1.8294 0.13913 0.13481 -0.1708 0.0978 1.0000
18.000 1.8217 0.14454 0.14043 -0.1736 0.0949 1.0000
18.250 1.8195 0.14876 0.14476 -0.1758 0.0922 1.0000
18.500 1.8264 0.15088 0.14686 -0.1766 0.0892 1.0000
18.750 1.8101 0.15842 0.15474 -0.1813 0.0871 1.0000
19.000 1.7946 0.16590 0.16250 -0.1862 0.0848 1.0000
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Polar data table (+)
Polar graphs
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