S2060 8% (s2060-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2060 8% (s2060-il) Reynolds number: 100,000 Max Cl/Cd: 53.62 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2060-il-100000.txt Download as CSV file: xf-s2060-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4857 0.11096 0.10579 -0.0158 1.0000 0.0925
-9.500 -0.5024 0.10868 0.10364 -0.0216 1.0000 0.0946
-9.250 -0.5166 0.10581 0.10088 -0.0266 1.0000 0.0950
-9.000 -0.4806 0.09973 0.09468 -0.0195 1.0000 0.0990
-8.750 -0.4761 0.09647 0.09145 -0.0200 1.0000 0.1029
-8.500 -0.4870 0.09337 0.08845 -0.0238 1.0000 0.1074
-8.250 -0.5117 0.09051 0.08578 -0.0303 1.0000 0.1085
-8.000 -0.5046 0.08575 0.08106 -0.0288 1.0000 0.1102
-7.750 -0.4851 0.08264 0.07790 -0.0248 1.0000 0.1146
-7.500 -0.4079 0.06753 0.06312 -0.0269 1.0000 0.1286
-7.250 -0.5173 0.07377 0.06907 -0.0393 1.0000 0.1233
-7.000 -0.4987 0.07045 0.06586 -0.0335 1.0000 0.1259
-6.750 -0.4927 0.06727 0.06269 -0.0330 1.0000 0.1304
-6.500 -0.4984 0.06232 0.05762 -0.0379 1.0000 0.1387
-6.250 -0.4976 0.04482 0.03911 -0.0453 1.0000 0.0658
-6.000 -0.4871 0.03994 0.03391 -0.0449 1.0000 0.0629
-5.750 -0.4733 0.03565 0.02910 -0.0444 1.0000 0.0636
-5.500 -0.4561 0.03190 0.02468 -0.0435 1.0000 0.0658
-5.250 -0.4359 0.02858 0.02060 -0.0425 1.0000 0.0676
-5.000 -0.4162 0.02605 0.01799 -0.0417 1.0000 0.0742
-4.750 -0.3936 0.02389 0.01527 -0.0407 1.0000 0.0831
-4.500 -0.3713 0.02278 0.01389 -0.0397 1.0000 0.0947
-4.250 -0.3489 0.02127 0.01235 -0.0390 1.0000 0.1062
-4.000 -0.3255 0.01986 0.01082 -0.0381 1.0000 0.1161
-3.750 -0.3024 0.01886 0.00976 -0.0373 1.0000 0.1294
-3.500 -0.2789 0.01784 0.00871 -0.0365 1.0000 0.1427
-3.250 -0.2555 0.01705 0.00794 -0.0357 1.0000 0.1621
-3.000 -0.2323 0.01621 0.00725 -0.0350 1.0000 0.1880
-2.750 -0.2092 0.01536 0.00663 -0.0343 1.0000 0.2311
-2.500 -0.1866 0.01429 0.00617 -0.0338 1.0000 0.3271
-2.250 -0.1687 0.01300 0.00613 -0.0319 1.0000 0.5710
-2.000 -0.1577 0.01256 0.00632 -0.0273 1.0000 0.7635
-1.750 -0.1395 0.01231 0.00633 -0.0237 1.0000 0.9184
-1.500 -0.1029 0.01223 0.00599 -0.0262 1.0000 1.0000
-1.250 -0.0806 0.01236 0.00589 -0.0259 1.0000 1.0000
-1.000 -0.0584 0.01253 0.00587 -0.0256 1.0000 1.0000
-0.750 -0.0365 0.01274 0.00590 -0.0253 1.0000 1.0000
-0.500 -0.0148 0.01298 0.00599 -0.0249 1.0000 1.0000
-0.250 0.0066 0.01325 0.00615 -0.0246 1.0000 1.0000
0.000 0.0276 0.01357 0.00637 -0.0243 1.0000 1.0000
0.250 0.0661 0.01409 0.00677 -0.0273 0.9940 1.0000
0.500 0.1168 0.01465 0.00726 -0.0325 0.9835 1.0000
0.750 0.1652 0.01506 0.00763 -0.0371 0.9716 1.0000
1.000 0.2124 0.01538 0.00792 -0.0413 0.9589 1.0000
1.250 0.2592 0.01560 0.00815 -0.0453 0.9458 1.0000
1.500 0.3062 0.01572 0.00831 -0.0491 0.9323 1.0000
1.750 0.3538 0.01573 0.00839 -0.0527 0.9186 1.0000
2.000 0.4024 0.01561 0.00835 -0.0563 0.9048 1.0000
2.250 0.4508 0.01537 0.00824 -0.0596 0.8908 1.0000
2.500 0.4951 0.01504 0.00802 -0.0618 0.8754 1.0000
2.750 0.5365 0.01464 0.00774 -0.0632 0.8586 1.0000
3.000 0.5696 0.01433 0.00757 -0.0629 0.8375 1.0000
3.250 0.6027 0.01397 0.00730 -0.0624 0.8152 1.0000
3.500 0.6306 0.01373 0.00713 -0.0611 0.7876 1.0000
3.750 0.6577 0.01354 0.00696 -0.0595 0.7564 1.0000
4.000 0.6823 0.01347 0.00694 -0.0577 0.7184 1.0000
4.250 0.7067 0.01350 0.00694 -0.0559 0.6756 1.0000
4.500 0.7300 0.01368 0.00701 -0.0540 0.6265 1.0000
4.750 0.7517 0.01402 0.00719 -0.0520 0.5697 1.0000
5.000 0.7719 0.01451 0.00750 -0.0500 0.5063 1.0000
5.250 0.7903 0.01516 0.00784 -0.0478 0.4336 1.0000
5.500 0.8068 0.01600 0.00826 -0.0457 0.3487 1.0000
5.750 0.8230 0.01705 0.00885 -0.0439 0.2601 1.0000
6.000 0.8365 0.01880 0.00990 -0.0420 0.1506 1.0000
6.250 0.8480 0.02142 0.01195 -0.0393 0.0874 1.0000
6.500 0.8667 0.02315 0.01360 -0.0376 0.0730 1.0000
6.750 0.8875 0.02490 0.01529 -0.0364 0.0645 1.0000
7.000 0.9116 0.02665 0.01712 -0.0354 0.0597 1.0000
7.250 0.9367 0.02884 0.01932 -0.0348 0.0567 1.0000
7.500 0.9631 0.03222 0.02280 -0.0344 0.0549 1.0000
7.750 0.9861 0.03482 0.02585 -0.0333 0.0542 1.0000
8.000 1.0053 0.03736 0.02889 -0.0317 0.0529 1.0000
8.250 1.0215 0.04021 0.03225 -0.0300 0.0514 1.0000
8.500 1.0344 0.04399 0.03653 -0.0282 0.0518 1.0000
8.750 1.0435 0.04822 0.04121 -0.0263 0.0527 1.0000
9.000 1.0497 0.05298 0.04633 -0.0246 0.0539 1.0000
9.250 1.0604 0.05733 0.05097 -0.0232 0.0560 1.0000
9.500 1.0251 0.06447 0.05915 -0.0192 0.0627 1.0000
9.750 1.0139 0.07060 0.06560 -0.0178 0.0700 1.0000
10.000 0.9689 0.07648 0.07180 -0.0166 0.0728 1.0000
10.250 0.8795 0.07120 0.06675 -0.0114 0.0638 1.0000
10.500 0.8487 0.07801 0.07366 -0.0141 0.0643 1.0000
10.750 0.8254 0.08549 0.08121 -0.0175 0.0654 1.0000
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Polar data table (+)
Polar graphs
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