S1210 12% (s1210-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1210 12% (s1210-il) Reynolds number: 50,000 Max Cl/Cd: 42.15 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1210-il-50000-n5.txt Download as CSV file: xf-s1210-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.1678 0.10774 0.10191 -0.0418 0.9704 0.1176
-6.250 -0.1520 0.10424 0.09841 -0.0457 0.9599 0.1179
-5.750 -0.1495 0.09120 0.08532 -0.0606 0.9286 0.0579
-5.500 -0.1296 0.08700 0.08112 -0.0646 0.9179 0.0576
-5.250 -0.1103 0.08331 0.07744 -0.0676 0.9063 0.0568
-5.000 -0.0938 0.07934 0.07346 -0.0712 0.8930 0.0558
-4.750 -0.0754 0.07498 0.06910 -0.0760 0.8799 0.0547
-4.500 -0.0522 0.06961 0.06371 -0.0834 0.8679 0.0535
-4.250 -0.0112 0.06085 0.05484 -0.0987 0.8594 0.0517
-4.000 0.1366 0.04041 0.03296 -0.1515 0.8596 0.0503
-3.750 0.2034 0.03648 0.02842 -0.1631 0.8513 0.0541
-3.500 0.2696 0.03340 0.02459 -0.1721 0.8455 0.0578
-3.250 0.3160 0.03156 0.02264 -0.1761 0.8363 0.0610
-3.000 0.3680 0.02993 0.02076 -0.1808 0.8287 0.0670
-2.750 0.4223 0.02848 0.01919 -0.1866 0.8189 0.0802
-2.500 0.5049 0.02630 0.01776 -0.1989 0.8128 0.1824
-2.250 0.5394 0.02744 0.01874 -0.1990 0.7995 0.3033
-2.000 0.5607 0.02838 0.01975 -0.1958 0.7870 0.3456
-1.750 0.6082 0.02803 0.01902 -0.1989 0.7780 0.3710
-1.500 0.6468 0.02779 0.01850 -0.2008 0.7652 0.3850
-1.250 0.6854 0.02752 0.01800 -0.2026 0.7537 0.3954
-1.000 0.7336 0.02708 0.01721 -0.2064 0.7443 0.4066
-0.750 0.7716 0.02697 0.01688 -0.2084 0.7322 0.4160
-0.500 0.8096 0.02688 0.01658 -0.2104 0.7211 0.4246
-0.250 0.8537 0.02668 0.01609 -0.2135 0.7120 0.4341
0.000 0.8849 0.02683 0.01613 -0.2142 0.7007 0.4422
0.250 0.9230 0.02690 0.01598 -0.2163 0.6916 0.4531
0.500 0.9552 0.02704 0.01603 -0.2171 0.6825 0.4616
0.750 0.9887 0.02724 0.01610 -0.2183 0.6736 0.4721
1.000 1.0224 0.02743 0.01619 -0.2195 0.6653 0.4846
1.250 1.0525 0.02772 0.01647 -0.2199 0.6572 0.4964
1.500 1.0840 0.02799 0.01671 -0.2207 0.6495 0.5098
1.750 1.1152 0.02830 0.01699 -0.2214 0.6424 0.5251
2.000 1.1433 0.02871 0.01745 -0.2216 0.6347 0.5423
2.250 1.1771 0.02893 0.01763 -0.2225 0.6289 0.5636
2.500 1.2004 0.02954 0.01837 -0.2220 0.6210 0.5848
2.750 1.2301 0.02984 0.01876 -0.2223 0.6149 0.6112
3.000 1.2548 0.03035 0.01940 -0.2218 0.6082 0.6413
3.250 1.2786 0.03083 0.02003 -0.2211 0.6015 0.6781
3.500 1.3061 0.03099 0.02029 -0.2206 0.5963 0.7292
3.750 1.3168 0.03161 0.02121 -0.2176 0.5890 0.7930
4.000 1.3321 0.03178 0.02149 -0.2150 0.5831 1.0000
4.250 1.3638 0.03249 0.02210 -0.2161 0.5767 1.0000
4.500 1.3874 0.03343 0.02306 -0.2158 0.5690 1.0000
4.750 1.4226 0.03378 0.02332 -0.2169 0.5630 1.0000
5.000 1.4382 0.03496 0.02463 -0.2153 0.5540 1.0000
5.250 1.4705 0.03531 0.02491 -0.2159 0.5472 1.0000
5.500 1.4860 0.03647 0.02623 -0.2142 0.5384 1.0000
5.750 1.5160 0.03686 0.02660 -0.2143 0.5313 1.0000
6.000 1.5310 0.03802 0.02790 -0.2125 0.5225 1.0000
6.250 1.5595 0.03840 0.02829 -0.2124 0.5149 1.0000
6.500 1.5728 0.03958 0.02966 -0.2103 0.5056 1.0000
6.750 1.6036 0.03970 0.02977 -0.2103 0.4975 1.0000
7.000 1.6117 0.04103 0.03130 -0.2074 0.4870 1.0000
7.250 1.6364 0.04134 0.03167 -0.2065 0.4777 1.0000
7.500 1.6510 0.04216 0.03263 -0.2044 0.4671 1.0000
7.750 1.6613 0.04322 0.03385 -0.2017 0.4564 1.0000
8.000 1.6857 0.04334 0.03400 -0.2006 0.4463 1.0000
8.250 1.6906 0.04459 0.03546 -0.1972 0.4349 1.0000
8.500 1.6938 0.04589 0.03694 -0.1937 0.4238 1.0000
8.750 1.7071 0.04644 0.03757 -0.1911 0.4129 1.0000
9.000 1.7079 0.04779 0.03908 -0.1873 0.4014 1.0000
9.250 1.6990 0.04999 0.04147 -0.1829 0.3896 1.0000
9.500 1.6976 0.05176 0.04339 -0.1794 0.3778 1.0000
9.750 1.7005 0.05325 0.04500 -0.1765 0.3658 1.0000
10.000 1.6917 0.05596 0.04788 -0.1732 0.3533 1.0000
10.250 1.6773 0.05962 0.05172 -0.1703 0.3405 1.0000
10.500 1.6689 0.06294 0.05517 -0.1681 0.3274 1.0000
10.750 1.6656 0.06588 0.05820 -0.1664 0.3145 1.0000
11.000 1.6670 0.06836 0.06074 -0.1649 0.3018 1.0000
11.250 1.6729 0.07033 0.06270 -0.1635 0.2896 1.0000
11.500 1.6729 0.07325 0.06568 -0.1623 0.2773 1.0000
11.750 1.6672 0.07720 0.06972 -0.1615 0.2654 1.0000
12.000 1.6672 0.08041 0.07297 -0.1607 0.2547 1.0000
12.250 1.6760 0.08226 0.07476 -0.1596 0.2448 1.0000
12.500 1.6690 0.08684 0.07949 -0.1594 0.2352 1.0000
12.750 1.6727 0.08975 0.08244 -0.1588 0.2268 1.0000
13.000 1.6736 0.09313 0.08590 -0.1585 0.2184 1.0000
13.250 1.6723 0.09701 0.08988 -0.1585 0.2109 1.0000
13.500 1.6738 0.10041 0.09340 -0.1584 0.2037 1.0000
13.750 1.6783 0.10344 0.09651 -0.1583 0.1976 1.0000
14.000 1.6685 0.10908 0.10239 -0.1595 0.1918 1.0000
14.250 1.6859 0.10980 0.10313 -0.1584 0.1866 1.0000
14.500 1.6731 0.11616 0.10973 -0.1603 0.1819 1.0000
14.750 1.6541 0.12383 0.11766 -0.1632 0.1770 1.0000
15.000 1.6722 0.12423 0.11809 -0.1621 0.1723 1.0000
15.250 1.6543 0.13194 0.12602 -0.1655 0.1683 1.0000
15.500 1.5704 0.15515 0.14956 -0.1795 0.1626 1.0000
15.750 1.5795 0.15739 0.15189 -0.1800 0.1590 1.0000
16.000 1.6173 0.15285 0.14743 -0.1757 0.1568 1.0000
16.250 1.4850 0.19456 0.18909 -0.2045 0.1469 1.0000
16.500 1.4985 0.19564 0.19030 -0.2045 0.1442 1.0000
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Polar data table (+)
Polar graphs
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