S2060 8% (s2060-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2060 8% (s2060-il) Reynolds number: 200,000 Max Cl/Cd: 62.89 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2060-il-200000-n5.txt Download as CSV file: xf-s2060-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2060 8%
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5217 0.08696 0.08333 -0.0244 1.0000 0.0118
-9.250 -0.5282 0.08163 0.07806 -0.0270 1.0000 0.0117
-9.000 -0.5378 0.07591 0.07240 -0.0301 1.0000 0.0116
-8.750 -0.5536 0.06947 0.06606 -0.0338 1.0000 0.0113
-8.250 -0.6411 0.03784 0.03365 -0.0509 1.0000 0.0102
-8.000 -0.6405 0.03284 0.02811 -0.0503 1.0000 0.0103
-7.750 -0.6318 0.02932 0.02412 -0.0493 1.0000 0.0104
-7.500 -0.6186 0.02667 0.02107 -0.0481 1.0000 0.0108
-7.250 -0.6029 0.02441 0.01844 -0.0469 1.0000 0.0112
-7.000 -0.5854 0.02254 0.01623 -0.0457 1.0000 0.0117
-6.750 -0.5666 0.02090 0.01426 -0.0445 1.0000 0.0124
-6.500 -0.5466 0.01968 0.01277 -0.0434 1.0000 0.0134
-6.250 -0.5264 0.01865 0.01163 -0.0425 1.0000 0.0148
-6.000 -0.5054 0.01784 0.01071 -0.0415 1.0000 0.0161
-5.750 -0.4840 0.01688 0.00958 -0.0405 1.0000 0.0178
-5.500 -0.4556 0.01591 0.00851 -0.0410 0.9982 0.0209
-5.250 -0.4224 0.01518 0.00763 -0.0423 0.9952 0.0266
-5.000 -0.3896 0.01480 0.00718 -0.0436 0.9918 0.0348
-4.750 -0.3567 0.01441 0.00678 -0.0450 0.9881 0.0441
-4.500 -0.3229 0.01401 0.00634 -0.0465 0.9849 0.0526
-4.250 -0.2900 0.01363 0.00583 -0.0477 0.9812 0.0597
-4.000 -0.2582 0.01315 0.00535 -0.0488 0.9766 0.0673
-3.750 -0.2242 0.01275 0.00494 -0.0502 0.9729 0.0776
-3.500 -0.1892 0.01239 0.00457 -0.0519 0.9697 0.0911
-3.250 -0.1590 0.01205 0.00424 -0.0525 0.9638 0.1076
-3.000 -0.1248 0.01170 0.00397 -0.0540 0.9596 0.1355
-2.750 -0.0886 0.01132 0.00372 -0.0560 0.9565 0.1743
-2.500 -0.0593 0.01095 0.00353 -0.0565 0.9497 0.2249
-2.250 -0.0260 0.01052 0.00333 -0.0578 0.9449 0.2938
-2.000 0.0050 0.01008 0.00319 -0.0587 0.9390 0.3789
-1.750 0.0347 0.00959 0.00309 -0.0592 0.9321 0.4843
-1.500 0.0642 0.00916 0.00304 -0.0594 0.9256 0.5946
-1.250 0.0921 0.00888 0.00302 -0.0590 0.9173 0.6787
-1.000 0.1197 0.00868 0.00299 -0.0585 0.9087 0.7399
-0.750 0.1482 0.00850 0.00293 -0.0580 0.9006 0.7905
-0.500 0.1736 0.00838 0.00289 -0.0569 0.8898 0.8352
-0.250 0.2011 0.00827 0.00283 -0.0561 0.8791 0.8769
0.000 0.2329 0.00817 0.00275 -0.0564 0.8683 0.9166
0.250 0.2716 0.00807 0.00264 -0.0582 0.8566 0.9536
0.500 0.3137 0.00799 0.00252 -0.0610 0.8430 0.9886
0.750 0.3441 0.00799 0.00246 -0.0614 0.8264 1.0000
1.000 0.3698 0.00802 0.00243 -0.0608 0.8081 1.0000
1.250 0.3957 0.00807 0.00241 -0.0602 0.7886 1.0000
1.500 0.4215 0.00814 0.00240 -0.0595 0.7668 1.0000
1.750 0.4472 0.00823 0.00240 -0.0589 0.7429 1.0000
2.000 0.4727 0.00835 0.00244 -0.0581 0.7160 1.0000
2.250 0.4980 0.00850 0.00249 -0.0574 0.6862 1.0000
2.500 0.5230 0.00868 0.00256 -0.0566 0.6533 1.0000
2.750 0.5475 0.00892 0.00265 -0.0558 0.6176 1.0000
3.000 0.5718 0.00918 0.00279 -0.0549 0.5786 1.0000
3.250 0.5957 0.00950 0.00295 -0.0541 0.5365 1.0000
3.500 0.6195 0.00985 0.00314 -0.0532 0.4937 1.0000
3.750 0.6431 0.01023 0.00336 -0.0524 0.4507 1.0000
4.000 0.6658 0.01071 0.00364 -0.0515 0.3970 1.0000
4.250 0.6870 0.01136 0.00395 -0.0505 0.3251 1.0000
4.500 0.7085 0.01206 0.00430 -0.0496 0.2559 1.0000
4.750 0.7309 0.01272 0.00469 -0.0488 0.1994 1.0000
5.000 0.7543 0.01329 0.00513 -0.0482 0.1598 1.0000
5.250 0.7764 0.01405 0.00563 -0.0475 0.1098 1.0000
5.500 0.7987 0.01481 0.00619 -0.0468 0.0690 1.0000
5.750 0.8200 0.01575 0.00691 -0.0459 0.0354 1.0000
6.000 0.8427 0.01650 0.00763 -0.0451 0.0262 1.0000
6.250 0.8661 0.01713 0.00837 -0.0444 0.0235 1.0000
6.500 0.8890 0.01783 0.00920 -0.0436 0.0216 1.0000
6.750 0.9109 0.01865 0.01011 -0.0426 0.0202 1.0000
7.000 0.9310 0.01969 0.01125 -0.0415 0.0192 1.0000
7.250 0.9510 0.02076 0.01242 -0.0403 0.0187 1.0000
7.500 0.9715 0.02176 0.01355 -0.0392 0.0181 1.0000
7.750 0.9921 0.02278 0.01469 -0.0382 0.0172 1.0000
8.000 1.0124 0.02385 0.01591 -0.0372 0.0163 1.0000
8.250 1.0320 0.02514 0.01733 -0.0361 0.0157 1.0000
8.500 1.0512 0.02656 0.01889 -0.0349 0.0153 1.0000
8.750 1.0700 0.02809 0.02058 -0.0338 0.0148 1.0000
9.000 1.0880 0.02978 0.02244 -0.0326 0.0145 1.0000
9.250 1.1048 0.03164 0.02450 -0.0314 0.0141 1.0000
9.500 1.1198 0.03379 0.02690 -0.0300 0.0138 1.0000
9.750 1.1319 0.03630 0.02968 -0.0285 0.0135 1.0000
10.000 1.1357 0.04019 0.03391 -0.0264 0.0130 1.0000
10.250 1.1425 0.04203 0.03611 -0.0243 0.0127 1.0000
10.500 1.1445 0.04438 0.03880 -0.0219 0.0124 1.0000
10.750 1.1389 0.04702 0.04175 -0.0189 0.0122 1.0000
11.000 1.1283 0.05000 0.04502 -0.0160 0.0121 1.0000
11.250 1.1149 0.05335 0.04864 -0.0140 0.0120 1.0000
11.500 1.0992 0.05723 0.05277 -0.0130 0.0120 1.0000
11.750 1.0812 0.06182 0.05760 -0.0135 0.0120 1.0000
12.000 1.0621 0.06727 0.06326 -0.0155 0.0120 1.0000
12.250 1.0413 0.07391 0.07011 -0.0193 0.0120 1.0000
12.500 1.0203 0.08175 0.07812 -0.0247 0.0121 1.0000
12.750 0.9980 0.09124 0.08776 -0.0317 0.0123 1.0000
13.000 0.9728 0.10291 0.09956 -0.0399 0.0124 1.0000
13.250 0.9466 0.11590 0.11261 -0.0480 0.0127 1.0000
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Polar data table (+)
Polar graphs
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