S2050 8.93% (s2050-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2050 8.93% (s2050-il) Reynolds number: 200,000 Max Cl/Cd: 58.21 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2050-il-200000-n5.txt Download as CSV file: xf-s2050-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2050 8.93%
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5850 0.08604 0.08237 -0.0231 1.0000 0.0114
-10.000 -0.6027 0.07782 0.07425 -0.0274 1.0000 0.0111
-9.750 -0.6555 0.05786 0.05427 -0.0420 1.0000 0.0105
-9.500 -0.6867 0.05097 0.04722 -0.0463 1.0000 0.0103
-9.250 -0.7113 0.04544 0.04141 -0.0470 1.0000 0.0102
-9.000 -0.7252 0.04014 0.03569 -0.0466 1.0000 0.0102
-8.750 -0.7278 0.03569 0.03076 -0.0457 1.0000 0.0102
-8.500 -0.7218 0.03215 0.02677 -0.0446 1.0000 0.0103
-8.250 -0.7104 0.02928 0.02348 -0.0435 1.0000 0.0105
-8.000 -0.6954 0.02689 0.02072 -0.0425 1.0000 0.0107
-7.750 -0.6780 0.02486 0.01837 -0.0415 1.0000 0.0110
-7.500 -0.6591 0.02313 0.01636 -0.0405 1.0000 0.0114
-7.250 -0.6389 0.02163 0.01460 -0.0396 1.0000 0.0119
-7.000 -0.6179 0.02039 0.01317 -0.0388 1.0000 0.0125
-6.750 -0.5967 0.01937 0.01209 -0.0381 1.0000 0.0137
-6.500 -0.5744 0.01852 0.01114 -0.0374 1.0000 0.0149
-6.250 -0.5518 0.01757 0.01004 -0.0367 1.0000 0.0160
-6.000 -0.5290 0.01662 0.00897 -0.0360 1.0000 0.0173
-5.750 -0.5057 0.01583 0.00811 -0.0354 1.0000 0.0196
-5.500 -0.4819 0.01509 0.00729 -0.0349 1.0000 0.0237
-5.250 -0.4580 0.01445 0.00667 -0.0344 1.0000 0.0326
-5.000 -0.4338 0.01395 0.00619 -0.0339 1.0000 0.0442
-4.750 -0.4095 0.01355 0.00581 -0.0335 1.0000 0.0566
-4.500 -0.3852 0.01322 0.00551 -0.0330 1.0000 0.0730
-4.250 -0.3608 0.01288 0.00518 -0.0326 1.0000 0.0869
-4.000 -0.3362 0.01256 0.00486 -0.0322 1.0000 0.1002
-3.750 -0.2994 0.01223 0.00457 -0.0344 0.9960 0.1200
-3.500 -0.2631 0.01191 0.00428 -0.0364 0.9916 0.1443
-3.250 -0.2268 0.01155 0.00404 -0.0385 0.9867 0.1786
-3.000 -0.1908 0.01114 0.00382 -0.0406 0.9818 0.2273
-2.500 -0.1207 0.01015 0.00339 -0.0443 0.9696 0.3803
-2.250 -0.0885 0.00962 0.00326 -0.0455 0.9613 0.4838
-2.000 -0.0567 0.00925 0.00328 -0.0462 0.9527 0.5862
-1.750 -0.0222 0.00911 0.00325 -0.0473 0.9446 0.6449
-1.500 0.0098 0.00901 0.00319 -0.0478 0.9334 0.6796
-1.250 0.0438 0.00893 0.00313 -0.0488 0.9222 0.7066
-1.000 0.0790 0.00885 0.00306 -0.0500 0.9099 0.7284
-0.750 0.1144 0.00876 0.00298 -0.0512 0.8956 0.7460
-0.500 0.1500 0.00869 0.00290 -0.0523 0.8787 0.7622
-0.250 0.1846 0.00864 0.00284 -0.0533 0.8595 0.7789
0.000 0.2164 0.00863 0.00280 -0.0536 0.8371 0.7943
0.250 0.2463 0.00865 0.00277 -0.0536 0.8134 0.8076
0.500 0.2740 0.00869 0.00275 -0.0531 0.7885 0.8198
0.750 0.3008 0.00877 0.00275 -0.0525 0.7633 0.8310
1.000 0.3266 0.00885 0.00277 -0.0517 0.7380 0.8406
1.250 0.3520 0.00895 0.00279 -0.0509 0.7122 0.8496
1.500 0.3774 0.00905 0.00282 -0.0501 0.6854 0.8594
1.750 0.4017 0.00915 0.00286 -0.0491 0.6581 0.8692
2.000 0.4258 0.00927 0.00292 -0.0480 0.6300 0.8794
2.250 0.4501 0.00940 0.00297 -0.0471 0.6009 0.8902
2.750 0.4984 0.00970 0.00311 -0.0452 0.5400 0.9149
3.000 0.5233 0.00987 0.00321 -0.0444 0.5080 0.9305
3.250 0.5508 0.01007 0.00332 -0.0443 0.4732 0.9489
3.500 0.5820 0.01032 0.00345 -0.0451 0.4363 0.9745
3.750 0.6107 0.01062 0.00365 -0.0455 0.4008 1.0000
4.000 0.6364 0.01098 0.00388 -0.0453 0.3656 1.0000
4.250 0.6619 0.01137 0.00413 -0.0451 0.3289 1.0000
4.500 0.6869 0.01181 0.00441 -0.0448 0.2911 1.0000
4.750 0.7122 0.01224 0.00475 -0.0445 0.2555 1.0000
5.000 0.7374 0.01269 0.00509 -0.0442 0.2246 1.0000
5.250 0.7623 0.01318 0.00548 -0.0439 0.1934 1.0000
5.500 0.7866 0.01375 0.00590 -0.0435 0.1585 1.0000
5.750 0.8101 0.01443 0.00640 -0.0431 0.1210 1.0000
6.000 0.8339 0.01508 0.00691 -0.0427 0.0917 1.0000
6.250 0.8575 0.01575 0.00747 -0.0422 0.0698 1.0000
6.500 0.8814 0.01639 0.00808 -0.0417 0.0535 1.0000
6.750 0.9047 0.01710 0.00878 -0.0411 0.0412 1.0000
7.000 0.9274 0.01792 0.00964 -0.0404 0.0331 1.0000
7.250 0.9497 0.01874 0.01051 -0.0397 0.0283 1.0000
7.500 0.9712 0.01965 0.01150 -0.0388 0.0253 1.0000
7.750 0.9934 0.02045 0.01240 -0.0380 0.0229 1.0000
8.000 1.0146 0.02133 0.01337 -0.0372 0.0213 1.0000
8.250 1.0335 0.02251 0.01462 -0.0361 0.0201 1.0000
8.500 1.0519 0.02376 0.01601 -0.0349 0.0193 1.0000
8.750 1.0710 0.02495 0.01734 -0.0338 0.0187 1.0000
9.000 1.0894 0.02626 0.01881 -0.0326 0.0181 1.0000
9.250 1.1073 0.02767 0.02038 -0.0314 0.0175 1.0000
9.500 1.1247 0.02906 0.02193 -0.0302 0.0168 1.0000
9.750 1.1415 0.03038 0.02339 -0.0291 0.0160 1.0000
10.000 1.1568 0.03176 0.02491 -0.0278 0.0153 1.0000
10.250 1.1698 0.03346 0.02675 -0.0264 0.0148 1.0000
10.500 1.1797 0.03572 0.02919 -0.0248 0.0144 1.0000
10.750 1.1865 0.03833 0.03204 -0.0229 0.0142 1.0000
11.000 1.1909 0.04049 0.03448 -0.0207 0.0140 1.0000
11.250 1.1903 0.04282 0.03709 -0.0182 0.0138 1.0000
11.500 1.1857 0.04543 0.03998 -0.0157 0.0137 1.0000
11.750 1.1777 0.04840 0.04322 -0.0138 0.0135 1.0000
12.000 1.1668 0.05184 0.04693 -0.0128 0.0134 1.0000
12.250 1.1540 0.05582 0.05116 -0.0128 0.0134 1.0000
12.500 1.1387 0.06057 0.05617 -0.0141 0.0133 1.0000
12.750 1.1212 0.06625 0.06208 -0.0168 0.0133 1.0000
13.000 1.1027 0.07286 0.06890 -0.0207 0.0133 1.0000
13.250 1.0822 0.08064 0.07688 -0.0260 0.0134 1.0000
13.500 1.0596 0.08972 0.08615 -0.0324 0.0135 1.0000
13.750 1.0351 0.10010 0.09668 -0.0396 0.0136 1.0000
14.000 1.0083 0.11188 0.10859 -0.0474 0.0138 1.0000
14.250 0.9758 0.12623 0.12304 -0.0563 0.0140 1.0000
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Polar data table (+)
Polar graphs
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