S2055 (s2055-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2055 (s2055-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.04 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2055-il-1000000-n5.txt Download as CSV file: xf-s2055-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2055
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5139 0.08888 0.08724 -0.0244 1.0000 0.0024
-9.500 -0.5281 0.08187 0.08026 -0.0276 1.0000 0.0023
-9.000 -0.7299 0.02530 0.02235 -0.0492 0.9929 0.0023
-8.750 -0.7111 0.02206 0.01871 -0.0495 0.9900 0.0024
-8.500 -0.6836 0.02126 0.01782 -0.0503 0.9882 0.0025
-8.250 -0.6579 0.01942 0.01572 -0.0510 0.9864 0.0026
-8.000 -0.6301 0.01807 0.01416 -0.0518 0.9851 0.0028
-7.750 -0.6011 0.01699 0.01292 -0.0528 0.9839 0.0029
-7.500 -0.5732 0.01565 0.01135 -0.0534 0.9824 0.0030
-7.250 -0.5491 0.01462 0.01015 -0.0530 0.9788 0.0031
-7.000 -0.5222 0.01379 0.00915 -0.0532 0.9758 0.0033
-6.750 -0.4947 0.01294 0.00815 -0.0534 0.9732 0.0035
-6.500 -0.4665 0.01209 0.00716 -0.0537 0.9708 0.0036
-6.250 -0.4402 0.01151 0.00648 -0.0536 0.9674 0.0037
-6.000 -0.4147 0.01107 0.00596 -0.0532 0.9628 0.0039
-5.750 -0.3877 0.01063 0.00546 -0.0531 0.9589 0.0041
-5.500 -0.3619 0.00989 0.00457 -0.0528 0.9549 0.0046
-5.250 -0.3371 0.00939 0.00399 -0.0522 0.9490 0.0051
-5.000 -0.3105 0.00904 0.00360 -0.0519 0.9441 0.0058
-4.750 -0.2841 0.00876 0.00329 -0.0516 0.9386 0.0066
-4.500 -0.2577 0.00849 0.00297 -0.0513 0.9321 0.0073
-4.250 -0.2312 0.00821 0.00266 -0.0510 0.9257 0.0094
-4.000 -0.2045 0.00802 0.00244 -0.0507 0.9180 0.0123
-3.750 -0.1775 0.00790 0.00231 -0.0506 0.9101 0.0136
-3.250 -0.1241 0.00751 0.00183 -0.0500 0.8916 0.0182
-3.000 -0.0972 0.00738 0.00165 -0.0498 0.8814 0.0204
-2.750 -0.0706 0.00721 0.00148 -0.0495 0.8703 0.0294
-2.500 -0.0442 0.00702 0.00132 -0.0492 0.8579 0.0514
-2.250 -0.0176 0.00692 0.00120 -0.0489 0.8423 0.0646
-2.000 0.0087 0.00682 0.00109 -0.0485 0.8242 0.0837
-1.750 0.0348 0.00674 0.00100 -0.0482 0.8047 0.1074
-1.500 0.0607 0.00658 0.00090 -0.0478 0.7839 0.1521
-1.250 0.0865 0.00644 0.00082 -0.0475 0.7633 0.2022
-1.000 0.1125 0.00623 0.00076 -0.0472 0.7457 0.2697
-0.750 0.1377 0.00583 0.00070 -0.0470 0.7310 0.3967
-0.500 0.1628 0.00545 0.00066 -0.0466 0.7168 0.5217
-0.250 0.1886 0.00525 0.00063 -0.0463 0.7001 0.5966
0.000 0.2124 0.00489 0.00065 -0.0456 0.6834 0.7344
0.250 0.2371 0.00479 0.00070 -0.0448 0.6636 0.8038
0.500 0.2623 0.00483 0.00075 -0.0441 0.6382 0.8366
0.750 0.2880 0.00492 0.00079 -0.0436 0.6115 0.8588
1.000 0.3130 0.00506 0.00085 -0.0429 0.5750 0.8761
1.250 0.3376 0.00527 0.00092 -0.0422 0.5304 0.8901
1.500 0.3624 0.00547 0.00100 -0.0416 0.4901 0.9028
1.750 0.3867 0.00570 0.00110 -0.0409 0.4473 0.9155
2.000 0.4108 0.00593 0.00120 -0.0401 0.4074 0.9270
2.250 0.4350 0.00612 0.00129 -0.0393 0.3753 0.9376
2.500 0.4593 0.00634 0.00140 -0.0386 0.3409 0.9476
2.750 0.4839 0.00658 0.00151 -0.0379 0.3049 0.9568
3.000 0.5095 0.00688 0.00164 -0.0376 0.2616 0.9643
3.250 0.5364 0.00713 0.00177 -0.0376 0.2303 0.9711
3.500 0.5659 0.00735 0.00191 -0.0381 0.2082 0.9765
3.750 0.5951 0.00753 0.00204 -0.0385 0.1925 0.9822
4.000 0.6260 0.00780 0.00220 -0.0395 0.1664 0.9861
4.250 0.6564 0.00810 0.00238 -0.0403 0.1382 0.9908
4.500 0.6860 0.00849 0.00262 -0.0410 0.1042 0.9960
4.750 0.7141 0.00888 0.00288 -0.0414 0.0761 1.0000
5.000 0.7374 0.00918 0.00311 -0.0406 0.0600 1.0000
5.250 0.7615 0.00946 0.00335 -0.0400 0.0489 1.0000
5.500 0.7860 0.00975 0.00359 -0.0395 0.0400 1.0000
5.750 0.8105 0.01005 0.00386 -0.0390 0.0320 1.0000
6.000 0.8353 0.01033 0.00416 -0.0385 0.0260 1.0000
6.250 0.8598 0.01067 0.00446 -0.0381 0.0196 1.0000
6.500 0.8844 0.01100 0.00479 -0.0376 0.0165 1.0000
6.750 0.9087 0.01138 0.00518 -0.0370 0.0137 1.0000
7.000 0.9336 0.01166 0.00549 -0.0366 0.0128 1.0000
7.250 0.9582 0.01198 0.00585 -0.0362 0.0120 1.0000
7.500 0.9825 0.01234 0.00622 -0.0357 0.0109 1.0000
7.750 1.0066 0.01272 0.00665 -0.0352 0.0100 1.0000
8.000 1.0300 0.01318 0.00716 -0.0346 0.0089 1.0000
8.250 1.0538 0.01356 0.00759 -0.0341 0.0082 1.0000
8.500 1.0780 0.01389 0.00795 -0.0336 0.0076 1.0000
8.750 1.1018 0.01424 0.00832 -0.0331 0.0063 1.0000
9.000 1.1246 0.01470 0.00880 -0.0325 0.0051 1.0000
9.250 1.1472 0.01518 0.00932 -0.0318 0.0043 1.0000
9.500 1.1695 0.01569 0.00989 -0.0311 0.0036 1.0000
9.750 1.1908 0.01630 0.01053 -0.0303 0.0030 1.0000
10.000 1.2113 0.01698 0.01129 -0.0293 0.0026 1.0000
10.250 1.2319 0.01761 0.01200 -0.0284 0.0024 1.0000
10.500 1.2521 0.01825 0.01273 -0.0274 0.0023 1.0000
10.750 1.2712 0.01896 0.01355 -0.0263 0.0021 1.0000
11.000 1.2899 0.01970 0.01438 -0.0251 0.0020 1.0000
11.250 1.3075 0.02048 0.01525 -0.0238 0.0018 1.0000
11.500 1.3241 0.02132 0.01621 -0.0224 0.0017 1.0000
11.750 1.3391 0.02225 0.01724 -0.0208 0.0016 1.0000
12.000 1.3520 0.02329 0.01841 -0.0189 0.0015 1.0000
12.250 1.3620 0.02432 0.01957 -0.0166 0.0014 1.0000
12.500 1.3658 0.02565 0.02105 -0.0134 0.0013 1.0000
12.750 1.3654 0.02726 0.02284 -0.0099 0.0012 1.0000
13.000 1.3625 0.02908 0.02486 -0.0065 0.0012 1.0000
13.250 1.3606 0.03090 0.02684 -0.0037 0.0012 1.0000
13.500 1.3609 0.03263 0.02871 -0.0015 0.0011 1.0000
13.750 1.3576 0.03477 0.03100 0.0006 0.0011 1.0000
14.000 1.3528 0.03721 0.03360 0.0022 0.0011 1.0000
14.250 1.3459 0.04007 0.03662 0.0032 0.0011 1.0000
14.500 1.3374 0.04338 0.04009 0.0036 0.0011 1.0000
14.750 1.3254 0.04748 0.04435 0.0032 0.0011 1.0000
15.000 1.3101 0.05255 0.04959 0.0016 0.0011 1.0000
15.250 1.2944 0.05841 0.05561 -0.0012 0.0011 1.0000
15.500 1.2735 0.06612 0.06350 -0.0058 0.0011 1.0000
15.750 1.2467 0.07618 0.07374 -0.0123 0.0011 1.0000
16.000 1.2141 0.08820 0.08595 -0.0197 0.0011 1.0000
16.250 1.1624 0.10447 0.10240 -0.0291 0.0012 1.0000
16.500 1.1356 0.11524 0.11326 -0.0351 0.0011 1.0000
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