S8055 (12%) (s8055-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8055 (12%) (s8055-il) Reynolds number: 100,000 Max Cl/Cd: 50.78 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8055-il-100000.txt Download as CSV file: xf-s8055-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S8055 (12%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4031 0.09402 0.08930 -0.0385 1.0000 0.1279
-9.000 -0.4031 0.09092 0.08626 -0.0391 1.0000 0.1323
-8.750 -0.4598 0.08743 0.08302 -0.0457 1.0000 0.1371
-8.500 -0.5033 0.08644 0.08214 -0.0423 1.0000 0.1373
-8.250 -0.4437 0.08191 0.07759 -0.0391 1.0000 0.1424
-8.000 -0.4654 0.08039 0.07617 -0.0357 1.0000 0.1445
-7.750 -0.5004 0.07909 0.07498 -0.0320 1.0000 0.1449
-7.500 -0.5285 0.07725 0.07318 -0.0291 1.0000 0.1471
-7.250 -0.5978 0.07588 0.07160 -0.0281 1.0000 0.1524
-6.250 -0.6266 0.04937 0.04353 -0.0232 1.0000 0.0821
-6.000 -0.6159 0.04325 0.03695 -0.0211 1.0000 0.0643
-5.750 -0.6062 0.03893 0.03149 -0.0179 1.0000 0.0563
-5.500 -0.5908 0.03569 0.02800 -0.0165 1.0000 0.0553
-5.250 -0.5735 0.03317 0.02511 -0.0151 1.0000 0.0545
-5.000 -0.5547 0.03108 0.02265 -0.0136 1.0000 0.0546
-4.750 -0.5350 0.02966 0.02079 -0.0121 1.0000 0.0562
-4.500 -0.5148 0.02765 0.01865 -0.0110 1.0000 0.0584
-4.250 -0.4872 0.02631 0.01723 -0.0113 0.9979 0.0617
-4.000 -0.4506 0.02509 0.01583 -0.0127 0.9937 0.0661
-3.750 -0.4179 0.02381 0.01463 -0.0138 0.9888 0.0762
-3.500 -0.3831 0.02271 0.01366 -0.0153 0.9842 0.0981
-3.250 -0.3561 0.02138 0.01272 -0.0156 0.9786 0.1542
-3.000 -0.3325 0.01927 0.01228 -0.0157 0.9736 0.4093
-2.750 -0.3154 0.01856 0.01283 -0.0127 0.9677 0.6645
-2.500 -0.2930 0.01898 0.01347 -0.0100 0.9610 0.7898
-2.250 -0.2688 0.01950 0.01397 -0.0076 0.9544 0.8602
-2.000 -0.2243 0.02021 0.01456 -0.0089 0.9488 0.9175
-1.750 -0.1326 0.02134 0.01532 -0.0196 0.9473 0.9563
-1.500 -0.0255 0.02203 0.01566 -0.0345 0.9470 0.9774
-1.250 0.0673 0.02225 0.01561 -0.0474 0.9457 0.9949
-1.000 0.1145 0.02225 0.01548 -0.0524 0.9390 1.0000
-0.750 0.1510 0.02229 0.01540 -0.0551 0.9306 1.0000
-0.500 0.1742 0.02236 0.01539 -0.0553 0.9199 1.0000
-0.250 0.2247 0.02239 0.01532 -0.0601 0.9136 1.0000
0.000 0.2437 0.02247 0.01535 -0.0593 0.9015 1.0000
0.250 0.2702 0.02256 0.01539 -0.0597 0.8908 1.0000
0.500 0.3233 0.02246 0.01524 -0.0646 0.8841 1.0000
0.750 0.3463 0.02252 0.01527 -0.0641 0.8718 1.0000
1.000 0.4067 0.02214 0.01487 -0.0696 0.8657 1.0000
1.250 0.4317 0.02202 0.01475 -0.0690 0.8532 1.0000
1.500 0.4532 0.02194 0.01466 -0.0677 0.8400 1.0000
1.750 0.4791 0.02173 0.01446 -0.0670 0.8280 1.0000
2.000 0.5250 0.02100 0.01374 -0.0690 0.8202 1.0000
2.250 0.5419 0.02082 0.01357 -0.0666 0.8062 1.0000
2.500 0.5604 0.02058 0.01334 -0.0642 0.7925 1.0000
2.750 0.5811 0.02024 0.01302 -0.0622 0.7793 1.0000
3.000 0.6049 0.01977 0.01259 -0.0604 0.7668 1.0000
3.250 0.6349 0.01905 0.01187 -0.0594 0.7557 1.0000
3.500 0.6574 0.01854 0.01138 -0.0574 0.7418 1.0000
3.750 0.6787 0.01807 0.01094 -0.0552 0.7264 1.0000
4.000 0.6987 0.01766 0.01055 -0.0529 0.7094 1.0000
4.250 0.7181 0.01731 0.01022 -0.0505 0.6899 1.0000
4.500 0.7420 0.01683 0.00974 -0.0487 0.6697 1.0000
4.750 0.7652 0.01648 0.00937 -0.0469 0.6459 1.0000
5.000 0.7885 0.01622 0.00903 -0.0451 0.6180 1.0000
5.250 0.8088 0.01619 0.00890 -0.0430 0.5842 1.0000
5.500 0.8284 0.01632 0.00887 -0.0408 0.5461 1.0000
5.750 0.8460 0.01666 0.00900 -0.0385 0.5047 1.0000
6.000 0.8626 0.01716 0.00923 -0.0363 0.4634 1.0000
6.250 0.8780 0.01778 0.00963 -0.0340 0.4236 1.0000
6.500 0.8941 0.01850 0.01010 -0.0319 0.3890 1.0000
6.750 0.9106 0.01927 0.01066 -0.0300 0.3582 1.0000
7.000 0.9277 0.02005 0.01131 -0.0283 0.3311 1.0000
7.250 0.9459 0.02089 0.01199 -0.0269 0.3080 1.0000
7.500 0.9642 0.02170 0.01273 -0.0255 0.2869 1.0000
7.750 0.9828 0.02255 0.01347 -0.0242 0.2679 1.0000
8.000 1.0022 0.02346 0.01426 -0.0230 0.2506 1.0000
8.250 1.0212 0.02438 0.01512 -0.0219 0.2341 1.0000
8.500 1.0395 0.02530 0.01602 -0.0206 0.2186 1.0000
8.750 1.0579 0.02629 0.01697 -0.0194 0.2038 1.0000
9.000 1.0764 0.02730 0.01796 -0.0183 0.1900 1.0000
9.250 1.0928 0.02828 0.01905 -0.0167 0.1774 1.0000
9.500 1.1097 0.02942 0.02027 -0.0154 0.1657 1.0000
9.750 1.1284 0.03071 0.02160 -0.0144 0.1553 1.0000
10.000 1.1505 0.03206 0.02281 -0.0139 0.1455 1.0000
10.250 1.1632 0.03325 0.02428 -0.0120 0.1372 1.0000
10.500 1.1855 0.03496 0.02599 -0.0116 0.1300 1.0000
10.750 1.1987 0.03639 0.02767 -0.0099 0.1236 1.0000
11.000 1.2223 0.03824 0.02944 -0.0099 0.1175 1.0000
11.250 1.2295 0.03993 0.03152 -0.0074 0.1130 1.0000
11.500 1.2430 0.04169 0.03346 -0.0060 0.1089 1.0000
11.750 1.2666 0.04418 0.03591 -0.0062 0.1048 1.0000
12.000 1.2629 0.04629 0.03849 -0.0028 0.1025 1.0000
12.250 1.2593 0.04847 0.04101 0.0004 0.1000 1.0000
12.500 1.2597 0.05062 0.04337 0.0030 0.0975 1.0000
12.750 1.2629 0.05291 0.04583 0.0049 0.0954 1.0000
13.000 1.2830 0.05621 0.04910 0.0045 0.0925 1.0000
13.250 1.2616 0.05901 0.05223 0.0084 0.0919 1.0000
13.500 1.2368 0.06230 0.05584 0.0114 0.0914 1.0000
13.750 1.2116 0.06629 0.06012 0.0134 0.0912 1.0000
14.000 1.1827 0.07099 0.06509 0.0144 0.0911 1.0000
14.250 1.1516 0.07653 0.07086 0.0142 0.0913 1.0000
14.500 1.1178 0.08314 0.07768 0.0126 0.0916 1.0000
14.750 1.0827 0.09098 0.08568 0.0097 0.0921 1.0000
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Polar data table (+)
Polar graphs
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