S2055 (s2055-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2055 (s2055-il) Reynolds number: 50,000 Max Cl/Cd: 35.22 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2055-il-50000-n5.txt Download as CSV file: xf-s2055-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2055
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4783 0.09488 0.08788 -0.0265 1.0000 0.0490
-8.500 -0.4807 0.09068 0.08377 -0.0284 1.0000 0.0471
-8.250 -0.4867 0.08625 0.07944 -0.0310 1.0000 0.0454
-7.750 -0.5065 0.07595 0.06916 -0.0384 1.0000 0.0412
-7.500 -0.5067 0.07225 0.06547 -0.0383 1.0000 0.0407
-7.250 -0.5072 0.06854 0.06173 -0.0383 1.0000 0.0403
-7.000 -0.5078 0.06462 0.05775 -0.0381 1.0000 0.0398
-6.750 -0.5068 0.06074 0.05375 -0.0378 1.0000 0.0394
-6.500 -0.5040 0.05688 0.04971 -0.0372 1.0000 0.0391
-6.250 -0.4992 0.05303 0.04563 -0.0364 1.0000 0.0388
-6.000 -0.4923 0.04919 0.04141 -0.0354 1.0000 0.0387
-5.750 -0.4827 0.04556 0.03742 -0.0342 1.0000 0.0387
-5.500 -0.4706 0.04208 0.03347 -0.0329 1.0000 0.0397
-5.250 -0.4555 0.03899 0.02970 -0.0314 1.0000 0.0415
-5.000 -0.4409 0.03635 0.02694 -0.0303 1.0000 0.0445
-4.750 -0.4228 0.03398 0.02424 -0.0291 1.0000 0.0468
-4.500 -0.4025 0.03149 0.02129 -0.0277 1.0000 0.0485
-4.250 -0.3804 0.02920 0.01854 -0.0263 1.0000 0.0512
-4.000 -0.3590 0.02750 0.01656 -0.0251 1.0000 0.0577
-3.750 -0.3367 0.02608 0.01488 -0.0238 1.0000 0.0652
-3.500 -0.3140 0.02452 0.01318 -0.0224 1.0000 0.0708
-3.250 -0.2913 0.02334 0.01171 -0.0210 1.0000 0.0799
-3.000 -0.2693 0.02231 0.01071 -0.0201 1.0000 0.1003
-2.750 -0.2481 0.02122 0.00966 -0.0190 1.0000 0.1318
-2.500 -0.2278 0.01984 0.00884 -0.0183 1.0000 0.2174
-2.250 -0.2157 0.01764 0.00845 -0.0156 1.0000 0.5401
-2.000 -0.1278 0.01716 0.00840 -0.0228 1.0000 1.0000
-1.750 -0.1176 0.01713 0.00807 -0.0202 1.0000 1.0000
-1.500 -0.1054 0.01713 0.00779 -0.0180 1.0000 1.0000
-1.250 -0.0914 0.01717 0.00758 -0.0161 1.0000 1.0000
-1.000 -0.0759 0.01726 0.00742 -0.0144 1.0000 1.0000
-0.750 -0.0594 0.01737 0.00732 -0.0130 1.0000 1.0000
-0.500 -0.0421 0.01752 0.00724 -0.0117 1.0000 1.0000
-0.250 -0.0242 0.01771 0.00725 -0.0106 1.0000 1.0000
0.000 0.0028 0.01800 0.00737 -0.0113 0.9963 1.0000
0.250 0.0407 0.01840 0.00762 -0.0141 0.9875 1.0000
0.500 0.0789 0.01880 0.00788 -0.0168 0.9785 1.0000
0.750 0.1190 0.01923 0.00821 -0.0199 0.9695 1.0000
1.000 0.1563 0.01956 0.00848 -0.0224 0.9583 1.0000
1.250 0.1942 0.01986 0.00876 -0.0248 0.9463 1.0000
1.500 0.2332 0.02011 0.00901 -0.0274 0.9332 1.0000
1.750 0.2733 0.02030 0.00924 -0.0299 0.9190 1.0000
2.000 0.3155 0.02039 0.00941 -0.0326 0.9036 1.0000
2.250 0.3605 0.02035 0.00947 -0.0356 0.8878 1.0000
2.500 0.3965 0.02029 0.00952 -0.0368 0.8686 1.0000
2.750 0.4352 0.02013 0.00954 -0.0382 0.8503 1.0000
3.000 0.4723 0.01994 0.00949 -0.0391 0.8312 1.0000
3.250 0.5040 0.01979 0.00950 -0.0390 0.8089 1.0000
3.500 0.5349 0.01964 0.00951 -0.0387 0.7847 1.0000
3.750 0.5648 0.01949 0.00957 -0.0380 0.7570 1.0000
4.000 0.5940 0.01935 0.00959 -0.0372 0.7249 1.0000
4.250 0.6210 0.01929 0.00965 -0.0359 0.6855 1.0000
4.500 0.6479 0.01926 0.00969 -0.0346 0.6381 1.0000
4.750 0.6732 0.01940 0.00985 -0.0329 0.5798 1.0000
5.000 0.6966 0.01978 0.01003 -0.0311 0.5161 1.0000
5.250 0.7167 0.02046 0.01045 -0.0292 0.4546 1.0000
5.500 0.7351 0.02131 0.01106 -0.0273 0.3992 1.0000
5.750 0.7526 0.02224 0.01177 -0.0256 0.3493 1.0000
6.000 0.7699 0.02318 0.01259 -0.0239 0.3017 1.0000
6.250 0.7871 0.02417 0.01348 -0.0224 0.2571 1.0000
6.500 0.8036 0.02527 0.01457 -0.0209 0.2121 1.0000
6.750 0.8205 0.02654 0.01574 -0.0194 0.1675 1.0000
7.000 0.8370 0.02799 0.01699 -0.0181 0.1300 1.0000
7.250 0.8553 0.02962 0.01857 -0.0168 0.1055 1.0000
7.500 0.8738 0.03128 0.02025 -0.0156 0.0873 1.0000
7.750 0.8932 0.03316 0.02218 -0.0145 0.0766 1.0000
8.000 0.9139 0.03515 0.02436 -0.0134 0.0681 1.0000
8.250 0.9333 0.03724 0.02671 -0.0124 0.0602 1.0000
8.500 0.9519 0.03948 0.02910 -0.0113 0.0552 1.0000
8.750 0.9712 0.04255 0.03257 -0.0103 0.0523 1.0000
9.000 0.9859 0.04594 0.03655 -0.0088 0.0500 1.0000
9.250 0.9950 0.04930 0.04041 -0.0070 0.0476 1.0000
9.500 1.0015 0.05207 0.04346 -0.0054 0.0445 1.0000
9.750 1.0074 0.05513 0.04651 -0.0042 0.0416 1.0000
10.000 1.0013 0.05880 0.05073 -0.0019 0.0408 1.0000
10.250 0.9909 0.06274 0.05506 0.0003 0.0404 1.0000
10.500 0.9762 0.06649 0.05910 0.0024 0.0403 1.0000
10.750 0.9584 0.07060 0.06345 0.0034 0.0402 1.0000
11.000 0.9395 0.07522 0.06826 0.0030 0.0403 1.0000
11.250 0.9200 0.08050 0.07369 0.0012 0.0405 1.0000
11.500 0.9005 0.08663 0.07993 -0.0021 0.0408 1.0000
11.750 0.8824 0.09359 0.08696 -0.0065 0.0411 1.0000
12.000 0.8659 0.10138 0.09478 -0.0117 0.0414 1.0000
12.250 0.8530 0.10928 0.10269 -0.0166 0.0416 1.0000
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Polar data table (+)
Polar graphs
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