S4110 (s4110-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4110 (s4110-il) Reynolds number: 100,000 Max Cl/Cd: 60.11 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4110-il-100000.txt Download as CSV file: xf-s4110-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S4110
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3110 0.10307 0.09825 -0.0321 1.0000 0.0883
-9.250 -0.3256 0.10117 0.09645 -0.0348 1.0000 0.0890
-9.000 -0.3389 0.09895 0.09432 -0.0370 1.0000 0.0893
-8.750 -0.2990 0.09177 0.08706 -0.0314 1.0000 0.0931
-8.500 -0.2954 0.08879 0.08412 -0.0310 1.0000 0.0969
-8.250 -0.3033 0.08617 0.08158 -0.0319 1.0000 0.1012
-8.000 -0.3202 0.08409 0.07962 -0.0334 1.0000 0.1026
-7.750 -0.3414 0.08239 0.07805 -0.0339 1.0000 0.1030
-7.500 -0.3110 0.07667 0.07230 -0.0302 1.0000 0.1077
-7.250 -0.3139 0.07415 0.06984 -0.0288 1.0000 0.1110
-7.000 -0.3280 0.07219 0.06799 -0.0272 1.0000 0.1139
-6.750 -0.3496 0.07078 0.06671 -0.0250 1.0000 0.1152
-6.500 -0.3758 0.06893 0.06495 -0.0276 1.0000 0.1168
-6.250 -0.3965 0.06565 0.06161 -0.0342 1.0000 0.1176
-6.000 -0.3832 0.06236 0.05850 -0.0243 1.0000 0.1205
-5.750 -0.3833 0.05990 0.05607 -0.0221 1.0000 0.1234
-5.500 -0.3867 0.05685 0.05303 -0.0235 1.0000 0.1281
-5.250 -0.3895 0.05190 0.04797 -0.0295 1.0000 0.1340
-5.000 -0.3844 0.04941 0.04554 -0.0267 1.0000 0.1368
-4.750 -0.3752 0.04487 0.04079 -0.0328 1.0000 0.1482
-4.500 -0.3313 0.03858 0.03267 -0.0513 1.0000 0.0778
-4.250 -0.3058 0.03394 0.02757 -0.0524 1.0000 0.0697
-4.000 -0.2756 0.02920 0.02201 -0.0540 1.0000 0.0663
-3.750 -0.2495 0.02699 0.01938 -0.0542 1.0000 0.0690
-3.500 -0.2226 0.02529 0.01706 -0.0542 1.0000 0.0745
-3.250 -0.1966 0.02325 0.01480 -0.0542 1.0000 0.0802
-3.000 -0.1710 0.02186 0.01311 -0.0539 1.0000 0.0914
-2.750 -0.1482 0.02113 0.01238 -0.0535 1.0000 0.1095
-2.500 -0.1253 0.02058 0.01172 -0.0531 1.0000 0.1294
-2.250 -0.1022 0.01999 0.01104 -0.0526 1.0000 0.1459
-2.000 -0.0793 0.01943 0.01050 -0.0521 1.0000 0.1616
-1.750 -0.0422 0.01892 0.01016 -0.0544 0.9953 0.1875
-1.500 -0.0020 0.01837 0.00985 -0.0571 0.9887 0.2308
-1.250 0.0385 0.01726 0.00986 -0.0601 0.9836 0.4327
-1.000 0.0685 0.01584 0.00995 -0.0590 0.9756 1.0000
-0.750 0.1123 0.01627 0.01002 -0.0625 0.9675 1.0000
-0.500 0.1554 0.01663 0.01009 -0.0659 0.9585 1.0000
-0.250 0.1939 0.01692 0.01019 -0.0683 0.9485 1.0000
0.000 0.2368 0.01721 0.01030 -0.0714 0.9396 1.0000
0.250 0.2798 0.01742 0.01037 -0.0745 0.9301 1.0000
0.500 0.3173 0.01760 0.01045 -0.0764 0.9188 1.0000
0.750 0.3583 0.01772 0.01048 -0.0788 0.9086 1.0000
1.000 0.4077 0.01766 0.01037 -0.0826 0.9003 1.0000
1.250 0.4452 0.01767 0.01035 -0.0842 0.8883 1.0000
1.500 0.4865 0.01756 0.01022 -0.0863 0.8770 1.0000
1.750 0.5307 0.01729 0.00996 -0.0886 0.8669 1.0000
2.000 0.5747 0.01689 0.00958 -0.0905 0.8566 1.0000
2.250 0.6094 0.01665 0.00935 -0.0909 0.8431 1.0000
2.500 0.6434 0.01636 0.00909 -0.0909 0.8290 1.0000
2.750 0.6764 0.01604 0.00881 -0.0907 0.8140 1.0000
3.000 0.7086 0.01570 0.00849 -0.0902 0.7982 1.0000
3.250 0.7349 0.01555 0.00836 -0.0889 0.7782 1.0000
3.500 0.7634 0.01530 0.00814 -0.0878 0.7580 1.0000
3.750 0.7906 0.01511 0.00795 -0.0865 0.7356 1.0000
4.000 0.8179 0.01493 0.00775 -0.0853 0.7114 1.0000
4.250 0.8429 0.01487 0.00766 -0.0837 0.6829 1.0000
4.500 0.8671 0.01488 0.00767 -0.0822 0.6507 1.0000
4.750 0.8905 0.01499 0.00771 -0.0805 0.6140 1.0000
5.000 0.9132 0.01520 0.00780 -0.0788 0.5724 1.0000
5.250 0.9347 0.01555 0.00797 -0.0770 0.5259 1.0000
5.500 0.9546 0.01608 0.00830 -0.0752 0.4749 1.0000
5.750 0.9736 0.01680 0.00873 -0.0733 0.4231 1.0000
6.000 0.9918 0.01765 0.00930 -0.0715 0.3732 1.0000
6.250 1.0102 0.01862 0.01000 -0.0698 0.3296 1.0000
6.500 1.0290 0.01965 0.01078 -0.0683 0.2927 1.0000
6.750 1.0485 0.02073 0.01165 -0.0670 0.2623 1.0000
7.000 1.0684 0.02176 0.01258 -0.0658 0.2355 1.0000
7.250 1.0888 0.02283 0.01360 -0.0646 0.2127 1.0000
7.500 1.1092 0.02394 0.01459 -0.0636 0.1930 1.0000
7.750 1.1301 0.02517 0.01576 -0.0626 0.1756 1.0000
8.000 1.1503 0.02635 0.01703 -0.0614 0.1591 1.0000
8.250 1.1710 0.02768 0.01838 -0.0604 0.1445 1.0000
8.500 1.1918 0.02915 0.01987 -0.0594 0.1316 1.0000
8.750 1.2123 0.03067 0.02137 -0.0585 0.1197 1.0000
9.000 1.2336 0.03229 0.02299 -0.0577 0.1096 1.0000
9.250 1.2510 0.03389 0.02494 -0.0562 0.1003 1.0000
9.500 1.2712 0.03608 0.02720 -0.0553 0.0928 1.0000
9.750 1.2880 0.03774 0.02906 -0.0538 0.0856 1.0000
10.000 1.3035 0.04024 0.03179 -0.0524 0.0796 1.0000
10.250 1.3168 0.04236 0.03422 -0.0506 0.0744 1.0000
10.500 1.3313 0.04518 0.03707 -0.0496 0.0694 1.0000
10.750 1.3332 0.04791 0.04040 -0.0466 0.0662 1.0000
11.000 1.3371 0.05094 0.04379 -0.0441 0.0634 1.0000
11.250 1.3477 0.05314 0.04606 -0.0428 0.0601 1.0000
11.500 1.3446 0.05741 0.05058 -0.0406 0.0580 1.0000
11.750 1.3279 0.06049 0.05410 -0.0367 0.0572 1.0000
12.000 1.3080 0.06393 0.05789 -0.0332 0.0568 1.0000
12.250 1.2861 0.06786 0.06212 -0.0307 0.0565 1.0000
12.500 1.2622 0.07244 0.06698 -0.0295 0.0565 1.0000
12.750 1.2373 0.07771 0.07249 -0.0297 0.0567 1.0000
13.000 1.2113 0.08379 0.07877 -0.0312 0.0570 1.0000
13.250 1.1853 0.09069 0.08582 -0.0340 0.0575 1.0000
13.500 1.1600 0.09846 0.09372 -0.0379 0.0580 1.0000
13.750 1.0421 0.13244 0.12796 -0.0624 0.0712 1.0000
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Polar data table (+)
Polar graphs
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