S2060 8% (s2060-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2060 8% (s2060-il) Reynolds number: 200,000 Max Cl/Cd: 70.85 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2060-il-200000.txt Download as CSV file: xf-s2060-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3943 0.08735 0.08394 -0.0248 1.0000 0.0519
-9.000 -0.4024 0.08264 0.07927 -0.0278 1.0000 0.0538
-8.750 -0.4162 0.07764 0.07434 -0.0324 1.0000 0.0548
-8.500 -0.4276 0.07255 0.06931 -0.0361 1.0000 0.0551
-8.250 -0.4406 0.06746 0.06427 -0.0399 1.0000 0.0551
-8.000 -0.4564 0.06261 0.05941 -0.0430 1.0000 0.0552
-7.750 -0.4694 0.05780 0.05452 -0.0448 1.0000 0.0552
-7.500 -0.5198 0.06498 0.06136 -0.0458 1.0000 0.0551
-7.250 -0.5211 0.06089 0.05708 -0.0464 1.0000 0.0553
-7.000 -0.5376 0.04435 0.04031 -0.0471 1.0000 0.0313
-6.750 -0.5357 0.03911 0.03476 -0.0465 1.0000 0.0298
-6.500 -0.5312 0.03304 0.02813 -0.0455 1.0000 0.0282
-6.250 -0.5196 0.02839 0.02287 -0.0443 1.0000 0.0280
-6.000 -0.5023 0.02616 0.02025 -0.0431 1.0000 0.0302
-5.750 -0.4834 0.02371 0.01729 -0.0418 1.0000 0.0316
-5.500 -0.4625 0.02175 0.01488 -0.0405 1.0000 0.0326
-5.250 -0.4417 0.01885 0.01171 -0.0397 1.0000 0.0354
-5.000 -0.4195 0.01794 0.01066 -0.0387 1.0000 0.0406
-4.750 -0.3973 0.01686 0.00948 -0.0379 1.0000 0.0485
-4.500 -0.3745 0.01597 0.00844 -0.0370 1.0000 0.0580
-4.250 -0.3519 0.01582 0.00819 -0.0362 1.0000 0.0678
-4.000 -0.3290 0.01500 0.00741 -0.0356 1.0000 0.0774
-3.750 -0.3059 0.01435 0.00671 -0.0349 1.0000 0.0862
-3.500 -0.2827 0.01396 0.00624 -0.0341 1.0000 0.0954
-3.250 -0.2598 0.01347 0.00579 -0.0335 1.0000 0.1082
-3.000 -0.2367 0.01294 0.00534 -0.0329 1.0000 0.1246
-2.750 -0.2138 0.01254 0.00503 -0.0324 1.0000 0.1509
-2.500 -0.1817 0.01200 0.00481 -0.0339 0.9975 0.2083
-2.250 -0.1438 0.01134 0.00474 -0.0366 0.9932 0.3399
-2.000 -0.1091 0.01060 0.00480 -0.0386 0.9879 0.5359
-1.750 -0.0744 0.01026 0.00507 -0.0397 0.9830 0.7061
-1.500 -0.0446 0.01007 0.00515 -0.0395 0.9754 0.8029
-1.250 -0.0078 0.01000 0.00524 -0.0404 0.9706 0.8911
-1.000 0.0503 0.00985 0.00507 -0.0463 0.9680 1.0000
-0.750 0.0908 0.00986 0.00496 -0.0491 0.9606 1.0000
-0.500 0.1388 0.00986 0.00486 -0.0533 0.9564 1.0000
-0.250 0.1752 0.00979 0.00473 -0.0551 0.9470 1.0000
0.000 0.2250 0.00967 0.00456 -0.0594 0.9428 1.0000
0.250 0.2617 0.00956 0.00441 -0.0611 0.9331 1.0000
0.500 0.3046 0.00938 0.00421 -0.0639 0.9265 1.0000
0.750 0.3399 0.00922 0.00404 -0.0650 0.9161 1.0000
1.000 0.3717 0.00908 0.00390 -0.0654 0.9041 1.0000
1.250 0.4022 0.00895 0.00377 -0.0654 0.8913 1.0000
1.500 0.4309 0.00884 0.00365 -0.0651 0.8769 1.0000
1.750 0.4584 0.00876 0.00355 -0.0644 0.8611 1.0000
2.000 0.4854 0.00870 0.00349 -0.0637 0.8440 1.0000
2.250 0.5108 0.00868 0.00346 -0.0626 0.8235 1.0000
2.500 0.5366 0.00868 0.00343 -0.0617 0.8016 1.0000
2.750 0.5618 0.00872 0.00343 -0.0606 0.7760 1.0000
3.000 0.5869 0.00878 0.00347 -0.0596 0.7473 1.0000
3.250 0.6117 0.00890 0.00350 -0.0585 0.7152 1.0000
3.500 0.6360 0.00907 0.00359 -0.0574 0.6783 1.0000
3.750 0.6600 0.00932 0.00371 -0.0563 0.6375 1.0000
4.000 0.6830 0.00964 0.00388 -0.0550 0.5891 1.0000
4.250 0.7052 0.01005 0.00408 -0.0537 0.5334 1.0000
4.500 0.7256 0.01061 0.00432 -0.0521 0.4616 1.0000
4.750 0.7456 0.01127 0.00463 -0.0507 0.3873 1.0000
5.000 0.7664 0.01195 0.00503 -0.0496 0.3187 1.0000
5.250 0.7875 0.01267 0.00547 -0.0486 0.2542 1.0000
5.500 0.8085 0.01349 0.00599 -0.0477 0.1892 1.0000
5.750 0.8243 0.01516 0.00692 -0.0461 0.0754 1.0000
6.000 0.8428 0.01661 0.00818 -0.0445 0.0466 1.0000
6.250 0.8628 0.01778 0.00943 -0.0431 0.0410 1.0000
6.500 0.8838 0.01882 0.01055 -0.0419 0.0378 1.0000
6.750 0.9043 0.02003 0.01179 -0.0407 0.0356 1.0000
7.000 0.9234 0.02199 0.01375 -0.0393 0.0333 1.0000
7.250 0.9463 0.02333 0.01522 -0.0384 0.0318 1.0000
7.500 0.9698 0.02495 0.01702 -0.0375 0.0310 1.0000
7.750 0.9931 0.02689 0.01917 -0.0366 0.0303 1.0000
8.000 1.0154 0.02920 0.02176 -0.0356 0.0301 1.0000
8.250 1.0356 0.03198 0.02488 -0.0343 0.0301 1.0000
8.500 1.0523 0.03523 0.02855 -0.0327 0.0305 1.0000
8.750 1.0660 0.03828 0.03202 -0.0308 0.0302 1.0000
9.000 1.0762 0.04157 0.03573 -0.0288 0.0298 1.0000
9.250 1.0798 0.04608 0.04067 -0.0265 0.0307 1.0000
9.500 1.0778 0.05150 0.04642 -0.0244 0.0320 1.0000
12.250 0.7363 0.13423 0.13123 -0.0457 0.0668 1.0000
12.500 0.7093 0.14056 0.13753 -0.0524 0.0649 1.0000
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Polar data table (+)
Polar graphs
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