S1091 (s1091-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1091 (s1091-il) Reynolds number: 100,000 Max Cl/Cd: 69.9 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1091-il-100000-n5.txt Download as CSV file: xf-s1091-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1091
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
------ -------- --------- --------- -------- -------- --------
-6.750 -0.2870 0.09924 0.09457 -0.0171 1.0000 0.0287
-6.500 -0.2896 0.09781 0.09323 -0.0163 1.0000 0.0295
-6.250 -0.2886 0.09638 0.09189 -0.0166 1.0000 0.0302
-6.000 -0.2864 0.09515 0.09074 -0.0179 1.0000 0.0306
-5.750 -0.2817 0.09400 0.08966 -0.0203 1.0000 0.0309
-5.500 -0.2716 0.09243 0.08813 -0.0238 0.9997 0.0311
-5.000 -0.2286 0.08216 0.07790 -0.0298 0.9903 0.0325
-4.750 -0.2053 0.07806 0.07380 -0.0326 0.9854 0.0341
-4.500 -0.1765 0.07438 0.07011 -0.0379 0.9786 0.0361
-4.250 -0.1399 0.07053 0.06622 -0.0453 0.9728 0.0388
-4.000 -0.0810 0.06746 0.06299 -0.0600 0.9640 0.0426
-3.750 -0.0259 0.06321 0.05862 -0.0718 0.9591 0.0434
-3.500 -0.0173 0.05883 0.05432 -0.0700 0.9504 0.0447
-3.250 0.0134 0.05528 0.05075 -0.0734 0.9451 0.0468
-3.000 0.0487 0.05205 0.04747 -0.0783 0.9366 0.0495
-2.750 0.1313 0.04845 0.04346 -0.0947 0.9329 0.0560
-2.500 0.1616 0.04421 0.03919 -0.0979 0.9242 0.0567
-2.250 0.2025 0.03886 0.03368 -0.1018 0.9201 0.0296
-2.000 0.2446 0.03533 0.02997 -0.1066 0.9123 0.0289
-1.750 0.2954 0.03135 0.02567 -0.1126 0.9078 0.0291
-1.500 0.3415 0.02759 0.02153 -0.1171 0.9017 0.0282
-1.000 0.4329 0.02122 0.01397 -0.1239 0.8910 0.0270
-0.750 0.4700 0.01940 0.01160 -0.1252 0.8818 0.0289
-0.500 0.5081 0.01793 0.00974 -0.1266 0.8734 0.0329
-0.250 0.5462 0.01674 0.00835 -0.1280 0.8644 0.0361
0.000 0.5809 0.01602 0.00744 -0.1288 0.8526 0.0429
0.250 0.6158 0.01532 0.00665 -0.1297 0.8407 0.0530
0.500 0.6526 0.01465 0.00604 -0.1308 0.8287 0.1100
0.750 0.6863 0.01413 0.00600 -0.1319 0.8158 0.2874
1.000 0.7181 0.01380 0.00585 -0.1323 0.8021 0.4187
1.250 0.7507 0.01281 0.00556 -0.1328 0.7881 1.0000
1.500 0.7810 0.01291 0.00543 -0.1328 0.7732 1.0000
1.750 0.8101 0.01304 0.00536 -0.1326 0.7578 1.0000
2.000 0.8384 0.01319 0.00534 -0.1323 0.7421 1.0000
2.250 0.8659 0.01335 0.00536 -0.1318 0.7256 1.0000
2.500 0.8929 0.01353 0.00540 -0.1312 0.7084 1.0000
2.750 0.9193 0.01372 0.00547 -0.1305 0.6902 1.0000
3.000 0.9443 0.01393 0.00561 -0.1296 0.6697 1.0000
3.250 0.9695 0.01414 0.00571 -0.1286 0.6486 1.0000
3.500 0.9933 0.01438 0.00586 -0.1275 0.6248 1.0000
3.750 1.0170 0.01463 0.00601 -0.1263 0.5990 1.0000
4.000 1.0400 0.01490 0.00618 -0.1250 0.5703 1.0000
4.250 1.0625 0.01520 0.00642 -0.1236 0.5376 1.0000
4.500 1.0842 0.01556 0.00663 -0.1222 0.4999 1.0000
4.750 1.1051 0.01602 0.00687 -0.1206 0.4609 1.0000
5.000 1.1255 0.01656 0.00720 -0.1191 0.4220 1.0000
5.250 1.1456 0.01716 0.00761 -0.1175 0.3849 1.0000
5.500 1.1653 0.01781 0.00814 -0.1160 0.3486 1.0000
5.750 1.1849 0.01848 0.00866 -0.1145 0.3132 1.0000
6.000 1.2042 0.01919 0.00923 -0.1131 0.2793 1.0000
6.250 1.2232 0.01995 0.00984 -0.1116 0.2475 1.0000
6.500 1.2422 0.02072 0.01051 -0.1102 0.2177 1.0000
6.750 1.2604 0.02158 0.01128 -0.1087 0.1905 1.0000
7.000 1.2787 0.02245 0.01207 -0.1072 0.1673 1.0000
7.250 1.2962 0.02338 0.01292 -0.1057 0.1496 1.0000
7.750 1.3316 0.02521 0.01480 -0.1025 0.1260 1.0000
8.000 1.3485 0.02620 0.01588 -0.1008 0.1179 1.0000
8.250 1.3644 0.02725 0.01696 -0.0991 0.1112 1.0000
8.500 1.3809 0.02828 0.01809 -0.0974 0.1053 1.0000
8.750 1.3969 0.02933 0.01922 -0.0957 0.0998 1.0000
9.000 1.4114 0.03053 0.02045 -0.0938 0.0954 1.0000
9.250 1.4281 0.03162 0.02177 -0.0922 0.0914 1.0000
9.500 1.4438 0.03282 0.02310 -0.0905 0.0882 1.0000
9.750 1.4590 0.03411 0.02448 -0.0889 0.0856 1.0000
10.000 1.4752 0.03564 0.02606 -0.0875 0.0833 1.0000
10.250 1.4925 0.03705 0.02774 -0.0861 0.0811 1.0000
10.500 1.5083 0.03850 0.02945 -0.0845 0.0786 1.0000
10.750 1.5217 0.03992 0.03110 -0.0828 0.0759 1.0000
11.000 1.5343 0.04137 0.03268 -0.0810 0.0735 1.0000
11.250 1.5507 0.04327 0.03465 -0.0800 0.0715 1.0000
11.500 1.5625 0.04523 0.03695 -0.0781 0.0699 1.0000
11.750 1.5690 0.04717 0.03928 -0.0757 0.0680 1.0000
12.000 1.5725 0.04912 0.04156 -0.0731 0.0659 1.0000
12.250 1.5746 0.05098 0.04367 -0.0706 0.0637 1.0000
12.500 1.5773 0.05278 0.04564 -0.0684 0.0617 1.0000
12.750 1.5832 0.05480 0.04775 -0.0668 0.0595 1.0000
13.000 1.5751 0.05753 0.05087 -0.0643 0.0579 1.0000
13.250 1.5636 0.06060 0.05434 -0.0622 0.0561 1.0000
13.500 1.5526 0.06380 0.05787 -0.0608 0.0540 1.0000
13.750 1.5450 0.06622 0.06045 -0.0601 0.0512 1.0000
14.000 1.5409 0.06804 0.06214 -0.0601 0.0477 1.0000
14.250 1.5243 0.07290 0.06744 -0.0607 0.0459 1.0000
14.500 1.5089 0.07796 0.07284 -0.0621 0.0436 1.0000
14.750 1.4975 0.08241 0.07746 -0.0642 0.0404 1.0000
15.000 1.4873 0.08693 0.08195 -0.0670 0.0374 1.0000
15.250 1.4694 0.09402 0.08938 -0.0701 0.0363 1.0000
15.500 1.4499 0.10179 0.09742 -0.0740 0.0359 1.0000
15.750 1.4300 0.11006 0.10589 -0.0783 0.0363 1.0000
16.000 1.4096 0.11884 0.11484 -0.0831 0.0368 1.0000
16.250 1.3905 0.12769 0.12382 -0.0882 0.0374 1.0000
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Polar data table (+)
Polar graphs
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