S2027 (s2027-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2027 (s2027-il) Reynolds number: 100,000 Max Cl/Cd: 45.95 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2027-il-100000.txt Download as CSV file: xf-s2027-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S2027
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3613 0.10532 0.10065 -0.0370 1.0000 0.1395
-10.000 -0.3457 0.10250 0.09783 -0.0361 1.0000 0.1441
-9.750 -0.3900 0.09887 0.09440 -0.0439 1.0000 0.1515
-9.500 -0.3573 0.09502 0.09053 -0.0401 1.0000 0.1544
-9.250 -0.3467 0.09207 0.08760 -0.0397 1.0000 0.1579
-7.750 -0.5938 0.05941 0.05491 -0.0476 0.9911 0.0968
-7.500 -0.5916 0.04768 0.04165 -0.0514 0.9805 0.0674
-7.250 -0.5655 0.04298 0.03663 -0.0539 0.9729 0.0661
-7.000 -0.5385 0.03896 0.03217 -0.0558 0.9651 0.0642
-6.750 -0.5053 0.03543 0.02810 -0.0580 0.9581 0.0628
-6.500 -0.4751 0.03286 0.02505 -0.0591 0.9499 0.0624
-6.250 -0.4349 0.03055 0.02237 -0.0616 0.9438 0.0630
-6.000 -0.4018 0.02887 0.02043 -0.0625 0.9356 0.0647
-5.750 -0.3596 0.02723 0.01859 -0.0651 0.9297 0.0691
-5.500 -0.3265 0.02589 0.01735 -0.0664 0.9217 0.0746
-5.250 -0.2855 0.02463 0.01600 -0.0685 0.9155 0.0811
-5.000 -0.2581 0.02343 0.01491 -0.0687 0.9066 0.0939
-4.750 -0.2319 0.02110 0.01335 -0.0691 0.8993 0.1806
-4.500 -0.2185 0.01973 0.01301 -0.0675 0.8884 0.3675
-4.250 -0.1839 0.01941 0.01302 -0.0682 0.8826 0.4807
-4.000 -0.1654 0.01972 0.01348 -0.0658 0.8712 0.5459
-3.750 -0.1414 0.02010 0.01388 -0.0641 0.8620 0.5928
-3.500 -0.1112 0.02028 0.01402 -0.0633 0.8546 0.6274
-3.250 -0.0894 0.02051 0.01419 -0.0614 0.8445 0.6545
-3.000 -0.0583 0.02051 0.01409 -0.0608 0.8383 0.6819
-2.750 -0.0385 0.02073 0.01430 -0.0585 0.8277 0.7025
-2.500 -0.0081 0.02064 0.01410 -0.0576 0.8222 0.7260
-2.250 0.0103 0.02080 0.01423 -0.0553 0.8111 0.7452
-2.000 0.0335 0.02084 0.01422 -0.0535 0.8028 0.7636
-1.750 0.0579 0.02078 0.01409 -0.0519 0.7948 0.7819
-1.500 0.0784 0.02085 0.01410 -0.0500 0.7854 0.7998
-1.250 0.1045 0.02067 0.01384 -0.0486 0.7787 0.8177
-1.000 0.1238 0.02075 0.01387 -0.0467 0.7687 0.8351
-0.750 0.1519 0.02052 0.01354 -0.0455 0.7628 0.8512
-0.500 0.1725 0.02061 0.01361 -0.0439 0.7524 0.8676
-0.250 0.2050 0.02034 0.01323 -0.0435 0.7470 0.8834
0.000 0.2310 0.02045 0.01332 -0.0431 0.7364 0.8998
0.250 0.2700 0.02023 0.01299 -0.0444 0.7303 0.9146
0.500 0.3086 0.02026 0.01296 -0.0464 0.7205 0.9293
0.750 0.3538 0.02017 0.01279 -0.0495 0.7122 0.9428
1.000 0.4027 0.01999 0.01251 -0.0533 0.7041 0.9554
1.250 0.4576 0.01994 0.01240 -0.0588 0.6942 0.9653
1.500 0.5112 0.01955 0.01189 -0.0634 0.6870 0.9760
1.750 0.5601 0.01953 0.01186 -0.0683 0.6758 0.9887
2.000 0.6074 0.01940 0.01168 -0.0726 0.6663 1.0000
2.250 0.6212 0.01935 0.01156 -0.0708 0.6583 1.0000
2.500 0.6285 0.01963 0.01186 -0.0683 0.6485 1.0000
2.750 0.6442 0.01953 0.01165 -0.0664 0.6420 1.0000
3.000 0.6511 0.01994 0.01209 -0.0637 0.6316 1.0000
3.250 0.6703 0.02005 0.01211 -0.0623 0.6241 1.0000
3.500 0.6897 0.02029 0.01231 -0.0610 0.6147 1.0000
3.750 0.7108 0.02061 0.01260 -0.0601 0.6054 1.0000
4.000 0.7382 0.02063 0.01255 -0.0598 0.5979 1.0000
4.250 0.7588 0.02108 0.01303 -0.0589 0.5876 1.0000
4.500 0.7874 0.02112 0.01299 -0.0587 0.5802 1.0000
4.750 0.8098 0.02149 0.01339 -0.0580 0.5701 1.0000
5.000 0.8334 0.02186 0.01379 -0.0575 0.5607 1.0000
5.250 0.8625 0.02191 0.01378 -0.0574 0.5529 1.0000
5.500 0.8833 0.02242 0.01437 -0.0566 0.5424 1.0000
5.750 0.9109 0.02261 0.01454 -0.0563 0.5342 1.0000
6.000 0.9354 0.02292 0.01488 -0.0558 0.5246 1.0000
6.250 0.9576 0.02340 0.01544 -0.0551 0.5147 1.0000
6.500 0.9890 0.02340 0.01535 -0.0553 0.5071 1.0000
6.750 1.0081 0.02401 0.01612 -0.0543 0.4961 1.0000
7.000 1.0319 0.02443 0.01659 -0.0537 0.4868 1.0000
7.250 1.0610 0.02453 0.01666 -0.0536 0.4781 1.0000
7.500 1.0800 0.02517 0.01744 -0.0526 0.4674 1.0000
7.750 1.1049 0.02551 0.01783 -0.0521 0.4581 1.0000
8.000 1.1321 0.02571 0.01803 -0.0518 0.4487 1.0000
8.250 1.1506 0.02634 0.01882 -0.0507 0.4380 1.0000
8.500 1.1748 0.02671 0.01923 -0.0501 0.4283 1.0000
8.750 1.2029 0.02684 0.01937 -0.0499 0.4185 1.0000
9.000 1.2197 0.02748 0.02017 -0.0485 0.4071 1.0000
9.250 1.2402 0.02789 0.02067 -0.0475 0.3959 1.0000
9.500 1.2637 0.02808 0.02088 -0.0467 0.3844 1.0000
9.750 1.2884 0.02817 0.02094 -0.0461 0.3723 1.0000
10.000 1.3073 0.02845 0.02131 -0.0448 0.3595 1.0000
10.250 1.3215 0.02888 0.02185 -0.0429 0.3463 1.0000
10.500 1.3351 0.02931 0.02238 -0.0410 0.3331 1.0000
10.750 1.3474 0.02975 0.02290 -0.0389 0.3197 1.0000
11.000 1.3575 0.03025 0.02347 -0.0367 0.3063 1.0000
11.250 1.3650 0.03083 0.02412 -0.0341 0.2930 1.0000
11.500 1.3681 0.03147 0.02484 -0.0310 0.2801 1.0000
11.750 1.3682 0.03227 0.02568 -0.0277 0.2673 1.0000
12.000 1.3651 0.03330 0.02674 -0.0245 0.2538 1.0000
12.250 1.3593 0.03463 0.02811 -0.0216 0.2400 1.0000
12.500 1.3509 0.03633 0.02985 -0.0190 0.2256 1.0000
12.750 1.3401 0.03847 0.03203 -0.0169 0.2107 1.0000
13.000 1.3284 0.04102 0.03461 -0.0152 0.1954 1.0000
13.250 1.3155 0.04400 0.03760 -0.0140 0.1798 1.0000
13.500 1.3018 0.04739 0.04097 -0.0133 0.1644 1.0000
13.750 1.2878 0.05112 0.04465 -0.0130 0.1498 1.0000
14.000 1.2741 0.05509 0.04858 -0.0130 0.1363 1.0000
14.250 1.2601 0.05939 0.05284 -0.0134 0.1235 1.0000
14.500 1.2486 0.06364 0.05703 -0.0138 0.1120 1.0000
14.750 1.2370 0.06809 0.06143 -0.0145 0.1013 1.0000
15.000 1.2279 0.07231 0.06555 -0.0152 0.0917 1.0000
15.250 1.2197 0.07666 0.06992 -0.0161 0.0832 1.0000
15.500 1.2140 0.08077 0.07406 -0.0167 0.0749 1.0000
15.750 1.2141 0.08395 0.07713 -0.0166 0.0674 1.0000
16.000 1.2117 0.08782 0.08109 -0.0174 0.0617 1.0000
16.250 1.2174 0.09040 0.08365 -0.0170 0.0564 1.0000
16.500 1.2126 0.09485 0.08831 -0.0184 0.0530 1.0000
16.750 1.2175 0.09764 0.09106 -0.0187 0.0497 1.0000
17.000 1.2270 0.10013 0.09361 -0.0180 0.0470 1.0000
17.250 1.2200 0.10521 0.09897 -0.0198 0.0460 1.0000
17.500 1.2111 0.11072 0.10474 -0.0221 0.0451 1.0000
17.750 1.1997 0.11678 0.11104 -0.0248 0.0445 1.0000
18.000 1.1845 0.12365 0.11815 -0.0284 0.0442 1.0000
18.250 1.1648 0.13167 0.12643 -0.0330 0.0443 1.0000
18.500 1.1397 0.14119 0.13620 -0.0389 0.0448 1.0000
18.750 1.1076 0.15292 0.14815 -0.0465 0.0456 1.0000
19.000 1.0726 0.16635 0.16172 -0.0553 0.0468 1.0000
19.250 1.0401 0.18062 0.17604 -0.0640 0.0479 1.0000
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