S2046 (s2046-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2046 (s2046-il) Reynolds number: 100,000 Max Cl/Cd: 58.02 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2046-il-100000.txt Download as CSV file: xf-s2046-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S2046
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4105 0.09781 0.09269 -0.0266 1.0000 0.1107
-8.500 -0.4286 0.09555 0.09057 -0.0310 1.0000 0.1147
-8.250 -0.4583 0.09334 0.08855 -0.0363 1.0000 0.1155
-8.000 -0.4172 0.08812 0.08323 -0.0299 1.0000 0.1190
-7.750 -0.4124 0.08537 0.08052 -0.0291 1.0000 0.1223
-7.500 -0.4212 0.08286 0.07811 -0.0293 1.0000 0.1264
-7.250 -0.4593 0.07776 0.07317 -0.0428 1.0000 0.1305
-7.000 -0.4406 0.07564 0.07112 -0.0343 1.0000 0.1325
-6.750 -0.4338 0.07325 0.06877 -0.0318 1.0000 0.1356
-6.500 -0.4545 0.06731 0.06275 -0.0442 1.0000 0.1454
-6.250 -0.4446 0.06475 0.06031 -0.0395 1.0000 0.1472
-6.000 -0.4389 0.04778 0.04222 -0.0558 1.0000 0.0863
-5.750 -0.4229 0.03983 0.03378 -0.0580 1.0000 0.0711
-5.500 -0.4036 0.03537 0.02893 -0.0591 1.0000 0.0682
-5.250 -0.3798 0.03105 0.02399 -0.0602 1.0000 0.0662
-5.000 -0.3554 0.02824 0.02069 -0.0606 1.0000 0.0673
-4.750 -0.3303 0.02624 0.01819 -0.0606 1.0000 0.0714
-4.500 -0.3039 0.02405 0.01549 -0.0606 1.0000 0.0744
-4.250 -0.2795 0.02235 0.01375 -0.0604 1.0000 0.0795
-4.000 -0.2531 0.02080 0.01194 -0.0600 1.0000 0.0887
-3.750 -0.2284 0.01975 0.01096 -0.0598 1.0000 0.1069
-3.500 -0.2036 0.01893 0.01008 -0.0597 1.0000 0.1321
-3.250 -0.1797 0.01839 0.00956 -0.0595 1.0000 0.1584
-3.000 -0.1557 0.01759 0.00894 -0.0592 1.0000 0.1805
-2.750 -0.1316 0.01694 0.00842 -0.0589 1.0000 0.2083
-2.500 -0.1069 0.01623 0.00799 -0.0588 1.0000 0.2515
-2.250 -0.0812 0.01504 0.00786 -0.0591 1.0000 0.4266
-2.000 -0.0631 0.01498 0.00834 -0.0570 1.0000 0.5935
-1.750 -0.0462 0.01519 0.00866 -0.0547 1.0000 0.6594
-1.500 -0.0296 0.01542 0.00894 -0.0525 1.0000 0.7072
-1.250 -0.0139 0.01562 0.00916 -0.0502 1.0000 0.7461
-1.000 0.0158 0.01593 0.00949 -0.0504 0.9941 0.7895
-0.750 0.0518 0.01613 0.00971 -0.0517 0.9842 0.8336
-0.500 0.0846 0.01611 0.00975 -0.0523 0.9735 0.8840
-0.250 0.1343 0.01594 0.00962 -0.0567 0.9623 1.0000
0.000 0.1871 0.01622 0.00973 -0.0625 0.9527 1.0000
0.250 0.2385 0.01642 0.00979 -0.0676 0.9425 1.0000
0.500 0.2834 0.01656 0.00982 -0.0713 0.9307 1.0000
0.750 0.3288 0.01665 0.00984 -0.0749 0.9193 1.0000
1.000 0.3768 0.01665 0.00979 -0.0787 0.9088 1.0000
1.250 0.4292 0.01650 0.00963 -0.0830 0.8994 1.0000
1.500 0.4710 0.01639 0.00951 -0.0852 0.8868 1.0000
1.750 0.5114 0.01622 0.00936 -0.0870 0.8738 1.0000
2.000 0.5502 0.01599 0.00915 -0.0883 0.8601 1.0000
2.250 0.5873 0.01571 0.00890 -0.0890 0.8455 1.0000
2.500 0.6224 0.01540 0.00863 -0.0892 0.8298 1.0000
2.750 0.6559 0.01508 0.00834 -0.0890 0.8129 1.0000
3.000 0.6848 0.01488 0.00816 -0.0881 0.7920 1.0000
3.250 0.7143 0.01464 0.00794 -0.0871 0.7697 1.0000
3.500 0.7415 0.01449 0.00778 -0.0858 0.7432 1.0000
3.750 0.7684 0.01437 0.00763 -0.0845 0.7132 1.0000
4.000 0.7947 0.01431 0.00746 -0.0830 0.6793 1.0000
4.250 0.8190 0.01438 0.00746 -0.0814 0.6379 1.0000
4.500 0.8429 0.01459 0.00750 -0.0799 0.5940 1.0000
4.750 0.8662 0.01493 0.00764 -0.0784 0.5494 1.0000
5.000 0.8891 0.01540 0.00791 -0.0771 0.5060 1.0000
5.250 0.9115 0.01595 0.00828 -0.0759 0.4639 1.0000
5.500 0.9335 0.01657 0.00876 -0.0746 0.4235 1.0000
5.750 0.9549 0.01724 0.00925 -0.0734 0.3830 1.0000
6.000 0.9754 0.01797 0.00982 -0.0721 0.3395 1.0000
6.250 0.9942 0.01882 0.01048 -0.0706 0.2874 1.0000
6.500 1.0110 0.02002 0.01136 -0.0690 0.2295 1.0000
6.750 1.0280 0.02146 0.01243 -0.0674 0.1849 1.0000
7.000 1.0471 0.02286 0.01360 -0.0661 0.1573 1.0000
7.250 1.0678 0.02443 0.01495 -0.0651 0.1405 1.0000
7.500 1.0902 0.02594 0.01637 -0.0643 0.1273 1.0000
7.750 1.1130 0.02724 0.01779 -0.0634 0.1164 1.0000
8.000 1.1377 0.02907 0.01968 -0.0629 0.1089 1.0000
8.250 1.1621 0.03076 0.02134 -0.0624 0.1020 1.0000
8.500 1.1852 0.03273 0.02353 -0.0616 0.0958 1.0000
8.750 1.2081 0.03464 0.02563 -0.0609 0.0909 1.0000
9.000 1.2321 0.03768 0.02868 -0.0607 0.0866 1.0000
9.250 1.2477 0.03961 0.03117 -0.0589 0.0825 1.0000
9.500 1.2651 0.04205 0.03393 -0.0576 0.0789 1.0000
9.750 1.2829 0.04479 0.03679 -0.0567 0.0757 1.0000
10.000 1.2914 0.04874 0.04113 -0.0550 0.0730 1.0000
10.250 1.2927 0.05191 0.04493 -0.0523 0.0708 1.0000
10.500 1.2905 0.05597 0.04949 -0.0497 0.0697 1.0000
10.750 1.2830 0.06011 0.05408 -0.0471 0.0687 1.0000
11.000 1.2701 0.06424 0.05858 -0.0444 0.0679 1.0000
11.250 1.2496 0.06825 0.06289 -0.0415 0.0677 1.0000
11.500 1.2220 0.07286 0.06776 -0.0393 0.0683 1.0000
11.750 1.1912 0.07847 0.07360 -0.0391 0.0693 1.0000
12.000 1.1607 0.08505 0.08037 -0.0409 0.0706 1.0000
12.250 1.1319 0.09264 0.08808 -0.0444 0.0718 1.0000
12.500 1.1068 0.10106 0.09659 -0.0490 0.0729 1.0000
12.750 1.0890 0.10967 0.10524 -0.0532 0.0737 1.0000
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Polar data table (+)
Polar graphs
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