S2050 8.93% (s2050-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2050 8.93% (s2050-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.75 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2050-il-1000000-n5.txt Download as CSV file: xf-s2050-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7487 0.09547 0.09358 -0.0172 1.0000 0.0034
-13.000 -0.8078 0.07955 0.07758 -0.0259 1.0000 0.0033
-12.750 -0.8650 0.06358 0.06154 -0.0354 1.0000 0.0032
-12.500 -0.9167 0.04494 0.04258 -0.0511 1.0000 0.0031
-12.250 -0.9329 0.03955 0.03703 -0.0549 1.0000 0.0031
-12.000 -0.9515 0.03572 0.03304 -0.0556 1.0000 0.0031
-11.750 -0.9719 0.03275 0.02988 -0.0531 1.0000 0.0031
-11.500 -0.9687 0.03093 0.02791 -0.0517 1.0000 0.0031
-11.250 -0.9661 0.02874 0.02552 -0.0501 1.0000 0.0032
-11.000 -0.9585 0.02687 0.02346 -0.0487 1.0000 0.0032
-10.750 -0.9465 0.02538 0.02181 -0.0474 1.0000 0.0032
-10.500 -0.9331 0.02391 0.02017 -0.0462 1.0000 0.0033
-10.250 -0.9173 0.02266 0.01875 -0.0451 1.0000 0.0033
-10.000 -0.9008 0.02139 0.01733 -0.0441 1.0000 0.0033
-9.750 -0.8826 0.02029 0.01609 -0.0431 1.0000 0.0034
-9.500 -0.8637 0.01922 0.01488 -0.0422 1.0000 0.0034
-9.250 -0.8436 0.01832 0.01386 -0.0414 1.0000 0.0034
-9.000 -0.8228 0.01745 0.01287 -0.0406 1.0000 0.0035
-8.750 -0.7996 0.01608 0.01132 -0.0406 0.9996 0.0036
-8.500 -0.7710 0.01495 0.01002 -0.0415 0.9986 0.0037
-8.250 -0.7416 0.01413 0.00911 -0.0424 0.9976 0.0039
-8.000 -0.7112 0.01352 0.00842 -0.0433 0.9965 0.0041
-7.750 -0.6803 0.01300 0.00785 -0.0443 0.9956 0.0043
-7.500 -0.6488 0.01245 0.00723 -0.0454 0.9947 0.0045
-7.250 -0.6190 0.01192 0.00662 -0.0461 0.9934 0.0048
-7.000 -0.5890 0.01144 0.00608 -0.0468 0.9918 0.0050
-6.750 -0.5581 0.01100 0.00558 -0.0477 0.9900 0.0052
-6.500 -0.5264 0.01061 0.00515 -0.0486 0.9883 0.0055
-6.250 -0.4938 0.01027 0.00477 -0.0498 0.9868 0.0056
-6.000 -0.4607 0.00982 0.00425 -0.0511 0.9853 0.0062
-5.750 -0.4267 0.00947 0.00387 -0.0525 0.9841 0.0070
-5.500 -0.3984 0.00917 0.00355 -0.0527 0.9810 0.0078
-5.250 -0.3685 0.00888 0.00324 -0.0532 0.9776 0.0095
-5.000 -0.3365 0.00850 0.00292 -0.0542 0.9747 0.0178
-4.750 -0.3030 0.00817 0.00265 -0.0555 0.9723 0.0286
-4.500 -0.2745 0.00793 0.00244 -0.0557 0.9670 0.0363
-4.250 -0.2445 0.00767 0.00223 -0.0562 0.9605 0.0474
-4.000 -0.2130 0.00744 0.00204 -0.0570 0.9533 0.0580
-3.750 -0.1785 0.00719 0.00184 -0.0585 0.9443 0.0736
-3.500 -0.1430 0.00693 0.00164 -0.0602 0.9305 0.0934
-3.250 -0.1093 0.00676 0.00145 -0.0614 0.9067 0.1082
-3.000 -0.0805 0.00666 0.00130 -0.0614 0.8736 0.1270
-2.750 -0.0541 0.00664 0.00119 -0.0610 0.8388 0.1449
-2.500 -0.0279 0.00659 0.00110 -0.0606 0.8079 0.1680
-2.000 0.0251 0.00643 0.00095 -0.0601 0.7570 0.2336
-1.750 0.0520 0.00633 0.00088 -0.0599 0.7346 0.2699
-1.500 0.0790 0.00621 0.00083 -0.0598 0.7136 0.3178
-1.250 0.1062 0.00611 0.00078 -0.0597 0.6929 0.3615
-1.000 0.1333 0.00598 0.00074 -0.0597 0.6706 0.4178
-0.750 0.1604 0.00584 0.00071 -0.0596 0.6475 0.4797
-0.500 0.1874 0.00572 0.00070 -0.0595 0.6225 0.5428
0.000 0.2417 0.00573 0.00077 -0.0592 0.5698 0.6364
0.250 0.2690 0.00583 0.00081 -0.0591 0.5438 0.6536
0.500 0.2964 0.00593 0.00085 -0.0589 0.5176 0.6671
0.750 0.3237 0.00605 0.00090 -0.0587 0.4919 0.6787
1.000 0.3510 0.00617 0.00096 -0.0586 0.4658 0.6912
1.250 0.3782 0.00630 0.00103 -0.0584 0.4391 0.7037
1.500 0.4055 0.00645 0.00110 -0.0583 0.4122 0.7138
1.750 0.4325 0.00661 0.00119 -0.0581 0.3828 0.7236
2.000 0.4596 0.00677 0.00128 -0.0579 0.3566 0.7331
2.250 0.4867 0.00695 0.00138 -0.0578 0.3308 0.7420
2.500 0.5137 0.00712 0.00149 -0.0576 0.3069 0.7493
2.750 0.5405 0.00734 0.00162 -0.0574 0.2766 0.7564
3.000 0.5670 0.00758 0.00176 -0.0572 0.2434 0.7640
3.500 0.6201 0.00806 0.00207 -0.0567 0.1902 0.7790
3.750 0.6462 0.00837 0.00226 -0.0564 0.1573 0.7855
4.000 0.6722 0.00868 0.00246 -0.0562 0.1284 0.7919
4.250 0.6986 0.00895 0.00266 -0.0559 0.1082 0.7995
4.500 0.7248 0.00921 0.00288 -0.0556 0.0897 0.8072
5.000 0.7766 0.00980 0.00337 -0.0550 0.0557 0.8241
5.250 0.8025 0.01009 0.00363 -0.0546 0.0436 0.8337
5.500 0.8281 0.01038 0.00391 -0.0542 0.0331 0.8450
5.750 0.8532 0.01072 0.00424 -0.0537 0.0224 0.8577
6.000 0.8780 0.01105 0.00457 -0.0532 0.0160 0.8716
6.500 0.9266 0.01155 0.00520 -0.0517 0.0126 0.9071
6.750 0.9482 0.01177 0.00552 -0.0503 0.0117 0.9379
7.000 0.9739 0.01206 0.00587 -0.0500 0.0109 1.0000
7.250 0.9992 0.01249 0.00635 -0.0496 0.0102 1.0000
7.500 1.0244 0.01291 0.00680 -0.0492 0.0099 1.0000
7.750 1.0499 0.01327 0.00720 -0.0488 0.0096 1.0000
8.000 1.0749 0.01367 0.00765 -0.0485 0.0093 1.0000
8.250 1.0996 0.01411 0.00815 -0.0480 0.0090 1.0000
8.500 1.1239 0.01459 0.00867 -0.0475 0.0087 1.0000
8.750 1.1479 0.01508 0.00922 -0.0470 0.0084 1.0000
9.000 1.1716 0.01560 0.00979 -0.0464 0.0081 1.0000
9.250 1.1948 0.01616 0.01040 -0.0458 0.0079 1.0000
9.500 1.2175 0.01676 0.01108 -0.0451 0.0077 1.0000
9.750 1.2392 0.01746 0.01184 -0.0443 0.0074 1.0000
10.000 1.2590 0.01837 0.01284 -0.0433 0.0070 1.0000
10.250 1.2781 0.01931 0.01388 -0.0421 0.0068 1.0000
10.500 1.2995 0.01994 0.01458 -0.0413 0.0067 1.0000
10.750 1.3200 0.02063 0.01535 -0.0404 0.0066 1.0000
11.000 1.3400 0.02133 0.01616 -0.0395 0.0065 1.0000
11.250 1.3595 0.02206 0.01697 -0.0385 0.0063 1.0000
11.500 1.3786 0.02278 0.01777 -0.0374 0.0061 1.0000
11.750 1.3965 0.02356 0.01863 -0.0362 0.0059 1.0000
12.000 1.4139 0.02433 0.01948 -0.0350 0.0057 1.0000
12.250 1.4299 0.02516 0.02040 -0.0337 0.0055 1.0000
12.500 1.4439 0.02609 0.02141 -0.0321 0.0054 1.0000
12.750 1.4551 0.02700 0.02240 -0.0300 0.0052 1.0000
13.000 1.4634 0.02794 0.02343 -0.0276 0.0051 1.0000
13.250 1.4705 0.02896 0.02455 -0.0252 0.0050 1.0000
13.500 1.4758 0.03015 0.02583 -0.0228 0.0049 1.0000
13.750 1.4787 0.03158 0.02735 -0.0206 0.0048 1.0000
14.000 1.4792 0.03329 0.02917 -0.0185 0.0047 1.0000
14.250 1.4742 0.03564 0.03165 -0.0168 0.0046 1.0000
14.500 1.4653 0.03865 0.03481 -0.0157 0.0045 1.0000
14.750 1.4592 0.04177 0.03807 -0.0154 0.0044 1.0000
15.000 1.4509 0.04554 0.04198 -0.0160 0.0044 1.0000
15.250 1.4477 0.04903 0.04559 -0.0170 0.0044 1.0000
15.500 1.4392 0.05361 0.05031 -0.0189 0.0044 1.0000
15.750 1.4227 0.05989 0.05676 -0.0222 0.0044 1.0000
16.000 1.4090 0.06620 0.06322 -0.0257 0.0043 1.0000
16.250 1.3934 0.07324 0.07040 -0.0298 0.0043 1.0000
16.500 1.3650 0.08311 0.08044 -0.0357 0.0043 1.0000
16.750 1.3216 0.09649 0.09402 -0.0438 0.0044 1.0000
17.000 1.2895 0.10803 0.10571 -0.0506 0.0044 1.0000
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Polar data table (+)
Polar graphs
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