S1210 12% (s1210-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1210 12% (s1210-il) Reynolds number: 200,000 Max Cl/Cd: 87.97 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1210-il-200000-n5.txt Download as CSV file: xf-s1210-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1054 0.10394 0.10042 -0.0664 0.9687 0.0311
-8.250 -0.0986 0.09996 0.09646 -0.0704 0.9616 0.0314
-8.000 -0.0893 0.09631 0.09282 -0.0731 0.9546 0.0315
-7.750 -0.0782 0.09212 0.08865 -0.0768 0.9483 0.0315
-7.000 -0.0515 0.07969 0.07624 -0.0799 0.9227 0.0213
-6.750 -0.0440 0.07663 0.07318 -0.0810 0.9113 0.0204
-6.500 -0.0351 0.07346 0.07002 -0.0828 0.9006 0.0201
-6.250 -0.0290 0.06886 0.06543 -0.0863 0.8893 0.0203
-6.000 -0.0209 0.06149 0.05805 -0.0937 0.8753 0.0207
-5.750 -0.0026 0.05598 0.05252 -0.1006 0.8621 0.0203
-5.500 0.1441 0.02501 0.01997 -0.1768 0.8560 0.0187
-5.250 0.2194 0.02117 0.01543 -0.1901 0.8472 0.0190
-5.000 0.2862 0.01881 0.01260 -0.1994 0.8356 0.0196
-4.750 0.3508 0.01718 0.01059 -0.2075 0.8201 0.0204
-4.500 0.4139 0.01605 0.00925 -0.2154 0.8007 0.0222
-4.000 0.5172 0.01473 0.00749 -0.2258 0.7536 0.0243
-3.750 0.5593 0.01438 0.00688 -0.2289 0.7301 0.0254
-3.500 0.5991 0.01406 0.00634 -0.2317 0.7080 0.0270
-3.250 0.6350 0.01388 0.00593 -0.2335 0.6876 0.0295
-3.000 0.6702 0.01371 0.00556 -0.2351 0.6694 0.0356
-2.750 0.7095 0.01332 0.00514 -0.2379 0.6533 0.0743
-2.500 0.7481 0.01299 0.00508 -0.2407 0.6390 0.2181
-2.250 0.7763 0.01326 0.00528 -0.2406 0.6265 0.2616
-2.000 0.8041 0.01356 0.00544 -0.2403 0.6148 0.2866
-1.750 0.8322 0.01375 0.00554 -0.2402 0.6043 0.2989
-1.500 0.8610 0.01387 0.00551 -0.2403 0.5947 0.3042
-1.250 0.8896 0.01396 0.00552 -0.2403 0.5850 0.3086
-1.000 0.9183 0.01408 0.00553 -0.2403 0.5765 0.3129
-0.750 0.9471 0.01419 0.00554 -0.2404 0.5682 0.3174
-0.500 0.9759 0.01431 0.00559 -0.2404 0.5614 0.3220
-0.250 1.0046 0.01441 0.00566 -0.2405 0.5544 0.3267
0.000 1.0332 0.01456 0.00573 -0.2405 0.5481 0.3317
0.250 1.0618 0.01469 0.00582 -0.2406 0.5419 0.3370
0.500 1.0903 0.01482 0.00594 -0.2406 0.5356 0.3421
0.750 1.1188 0.01500 0.00606 -0.2406 0.5304 0.3487
1.000 1.1475 0.01513 0.00621 -0.2407 0.5253 0.3558
1.250 1.1760 0.01529 0.00638 -0.2408 0.5199 0.3639
1.500 1.2043 0.01548 0.00654 -0.2408 0.5151 0.3723
1.750 1.2328 0.01565 0.00674 -0.2409 0.5106 0.3815
2.000 1.2612 0.01581 0.00694 -0.2409 0.5056 0.3915
2.500 1.3177 0.01623 0.00738 -0.2409 0.4969 0.4166
2.750 1.3456 0.01639 0.00763 -0.2409 0.4916 0.4320
3.000 1.3729 0.01658 0.00788 -0.2407 0.4852 0.4494
3.250 1.3999 0.01682 0.00812 -0.2405 0.4791 0.4686
3.500 1.4271 0.01698 0.00839 -0.2403 0.4728 0.4891
3.750 1.4543 0.01720 0.00867 -0.2401 0.4677 0.5123
4.000 1.4816 0.01745 0.00897 -0.2400 0.4631 0.5386
4.250 1.5082 0.01762 0.00930 -0.2397 0.4568 0.5694
4.500 1.5339 0.01785 0.00959 -0.2392 0.4501 0.6045
4.750 1.5590 0.01805 0.00992 -0.2386 0.4432 0.6449
5.000 1.5832 0.01825 0.01023 -0.2377 0.4358 0.6916
5.250 1.6058 0.01844 0.01054 -0.2366 0.4288 0.7506
5.500 1.6232 0.01850 0.01079 -0.2342 0.4211 0.8445
5.750 1.6397 0.01864 0.01098 -0.2318 0.4142 1.0000
6.000 1.6640 0.01893 0.01133 -0.2311 0.4058 1.0000
6.250 1.6872 0.01930 0.01168 -0.2302 0.3982 1.0000
6.500 1.7105 0.01961 0.01208 -0.2293 0.3887 1.0000
6.750 1.7328 0.01999 0.01248 -0.2282 0.3793 1.0000
7.000 1.7543 0.02038 0.01290 -0.2270 0.3687 1.0000
7.250 1.7756 0.02078 0.01336 -0.2258 0.3563 1.0000
7.500 1.7948 0.02126 0.01385 -0.2242 0.3411 1.0000
7.750 1.8109 0.02185 0.01441 -0.2220 0.3227 1.0000
8.000 1.8237 0.02258 0.01508 -0.2193 0.3024 1.0000
8.250 1.8343 0.02347 0.01590 -0.2163 0.2816 1.0000
8.500 1.8443 0.02448 0.01684 -0.2132 0.2628 1.0000
8.750 1.8535 0.02559 0.01790 -0.2101 0.2461 1.0000
9.000 1.8627 0.02674 0.01903 -0.2072 0.2312 1.0000
9.250 1.8715 0.02796 0.02023 -0.2042 0.2176 1.0000
9.500 1.8801 0.02921 0.02151 -0.2013 0.2056 1.0000
9.750 1.8877 0.03057 0.02290 -0.1984 0.1948 1.0000
10.000 1.8933 0.03210 0.02444 -0.1954 0.1848 1.0000
10.250 1.9000 0.03360 0.02599 -0.1926 0.1752 1.0000
10.500 1.9047 0.03531 0.02775 -0.1898 0.1665 1.0000
10.750 1.9083 0.03717 0.02965 -0.1870 0.1588 1.0000
11.000 1.9118 0.03911 0.03168 -0.1844 0.1522 1.0000
11.250 1.9144 0.04122 0.03386 -0.1820 0.1463 1.0000
11.500 1.9142 0.04369 0.03640 -0.1795 0.1416 1.0000
11.750 1.9178 0.04592 0.03875 -0.1776 0.1370 1.0000
12.000 1.9181 0.04857 0.04150 -0.1757 0.1329 1.0000
12.250 1.9156 0.05168 0.04468 -0.1739 0.1293 1.0000
12.500 1.9161 0.05457 0.04770 -0.1725 0.1262 1.0000
12.750 1.9173 0.05752 0.05080 -0.1714 0.1229 1.0000
13.000 1.9160 0.06088 0.05427 -0.1704 0.1195 1.0000
13.250 1.9126 0.06464 0.05811 -0.1696 0.1168 1.0000
13.500 1.9088 0.06852 0.06207 -0.1690 0.1144 1.0000
13.750 1.9104 0.07177 0.06549 -0.1685 0.1122 1.0000
14.000 1.9108 0.07524 0.06911 -0.1681 0.1095 1.0000
14.250 1.9095 0.07898 0.07297 -0.1679 0.1071 1.0000
14.500 1.9059 0.08315 0.07722 -0.1679 0.1042 1.0000
14.750 1.9006 0.08757 0.08167 -0.1680 0.1016 1.0000
15.000 1.9021 0.09108 0.08540 -0.1682 0.0984 1.0000
15.250 1.9011 0.09503 0.08949 -0.1686 0.0951 1.0000
15.500 1.8964 0.09959 0.09411 -0.1693 0.0915 1.0000
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Polar data table (+)
Polar graphs
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