S8037 (16%) (s8037-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8037 (16%) (s8037-il) Reynolds number: 50,000 Max Cl/Cd: 22.82 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8037-il-50000-n5.txt Download as CSV file: xf-s8037-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8037 (16%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3969 0.10450 0.09722 -0.0543 1.0000 0.0516
-11.500 -0.4056 0.09869 0.09149 -0.0568 1.0000 0.0514
-11.250 -0.4211 0.09153 0.08438 -0.0603 1.0000 0.0510
-11.000 -0.4423 0.08448 0.07736 -0.0641 1.0000 0.0504
-10.750 -0.4710 0.07785 0.07076 -0.0674 1.0000 0.0499
-10.500 -0.5011 0.07261 0.06549 -0.0688 1.0000 0.0492
-10.250 -0.5313 0.06856 0.06141 -0.0681 1.0000 0.0483
-10.000 -0.5615 0.06577 0.05859 -0.0651 1.0000 0.0481
-9.750 -0.5937 0.06395 0.05675 -0.0599 1.0000 0.0476
-9.500 -0.6260 0.06266 0.05546 -0.0536 1.0000 0.0474
-9.250 -0.6552 0.06149 0.05422 -0.0474 1.0000 0.0473
-9.000 -0.6653 0.05901 0.05153 -0.0451 0.9945 0.0477
-8.750 -0.6562 0.05532 0.04742 -0.0462 0.9824 0.0490
-8.500 -0.6467 0.05174 0.04334 -0.0464 0.9708 0.0503
-8.250 -0.6326 0.04850 0.03960 -0.0464 0.9604 0.0511
-8.000 -0.6159 0.04554 0.03608 -0.0460 0.9504 0.0522
-7.750 -0.5892 0.04324 0.03361 -0.0472 0.9434 0.0547
-7.500 -0.5664 0.04151 0.03168 -0.0474 0.9345 0.0577
-7.250 -0.5328 0.03928 0.02896 -0.0489 0.9292 0.0615
-7.000 -0.5069 0.03764 0.02726 -0.0490 0.9207 0.0643
-6.750 -0.4717 0.03611 0.02555 -0.0506 0.9153 0.0706
-6.500 -0.4412 0.03473 0.02413 -0.0514 0.9088 0.0769
-6.250 -0.4105 0.03350 0.02275 -0.0521 0.9020 0.0860
-6.000 -0.3757 0.03216 0.02140 -0.0538 0.8972 0.1000
-5.750 -0.3576 0.03123 0.02049 -0.0525 0.8882 0.1151
-5.500 -0.3317 0.03003 0.01938 -0.0528 0.8820 0.1428
-5.250 -0.3172 0.02898 0.01855 -0.0512 0.8735 0.1774
-5.000 -0.3010 0.02773 0.01771 -0.0500 0.8661 0.2395
-4.750 -0.2913 0.02664 0.01725 -0.0474 0.8583 0.3360
-4.500 -0.2798 0.02605 0.01726 -0.0442 0.8503 0.4535
-4.250 -0.2559 0.02592 0.01737 -0.0424 0.8450 0.5530
-4.000 -0.2456 0.02618 0.01767 -0.0385 0.8357 0.6068
-3.750 -0.2169 0.02637 0.01780 -0.0374 0.8305 0.6598
-3.500 -0.1972 0.02673 0.01808 -0.0349 0.8228 0.6975
-3.250 -0.1677 0.02706 0.01830 -0.0340 0.8167 0.7329
-3.000 -0.1253 0.02739 0.01845 -0.0351 0.8128 0.7657
-2.750 -0.1026 0.02779 0.01872 -0.0335 0.8047 0.7911
-2.500 -0.0612 0.02807 0.01880 -0.0352 0.7995 0.8122
-2.250 -0.0132 0.02817 0.01866 -0.0383 0.7956 0.8292
-2.000 0.0122 0.02849 0.01886 -0.0380 0.7874 0.8453
-1.750 0.0621 0.02865 0.01881 -0.0419 0.7824 0.8565
-1.500 0.1115 0.02861 0.01856 -0.0457 0.7784 0.8677
-1.250 0.1373 0.02894 0.01880 -0.0459 0.7698 0.8814
-1.000 0.1859 0.02900 0.01869 -0.0499 0.7646 0.8908
-0.750 0.2311 0.02895 0.01849 -0.0532 0.7599 0.9010
-0.500 0.2560 0.02933 0.01880 -0.0536 0.7510 0.9142
-0.250 0.3042 0.02924 0.01859 -0.0575 0.7460 0.9228
0.000 0.3362 0.02950 0.01878 -0.0591 0.7383 0.9344
0.250 0.3714 0.02959 0.01881 -0.0611 0.7314 0.9458
0.500 0.4189 0.02937 0.01847 -0.0649 0.7269 0.9542
0.750 0.4456 0.02985 0.01896 -0.0661 0.7171 0.9671
1.000 0.4889 0.02967 0.01871 -0.0693 0.7117 0.9764
1.250 0.5215 0.02997 0.01902 -0.0715 0.7028 0.9882
1.500 0.5644 0.02983 0.01884 -0.0749 0.6964 0.9974
1.750 0.5772 0.03016 0.01917 -0.0733 0.6880 1.0000
2.000 0.5860 0.03038 0.01936 -0.0706 0.6801 1.0000
2.250 0.5900 0.03078 0.01974 -0.0672 0.6717 1.0000
2.500 0.5976 0.03107 0.02000 -0.0642 0.6636 1.0000
2.750 0.6017 0.03151 0.02042 -0.0606 0.6550 1.0000
3.000 0.6113 0.03179 0.02068 -0.0578 0.6468 1.0000
3.250 0.6144 0.03233 0.02120 -0.0541 0.6377 1.0000
3.500 0.6297 0.03250 0.02133 -0.0520 0.6299 1.0000
3.750 0.6304 0.03321 0.02202 -0.0480 0.6200 1.0000
4.000 0.6526 0.03319 0.02200 -0.0468 0.6130 1.0000
4.250 0.6506 0.03407 0.02286 -0.0425 0.6023 1.0000
4.500 0.6799 0.03379 0.02258 -0.0421 0.5961 1.0000
4.750 0.6753 0.03481 0.02360 -0.0375 0.5845 1.0000
5.000 0.7116 0.03424 0.02305 -0.0379 0.5790 1.0000
5.250 0.7046 0.03538 0.02419 -0.0331 0.5667 1.0000
5.500 0.7197 0.03566 0.02449 -0.0310 0.5580 1.0000
5.750 0.7377 0.03578 0.02463 -0.0292 0.5490 1.0000
6.000 0.7349 0.03673 0.02559 -0.0249 0.5376 1.0000
6.250 0.7741 0.03598 0.02488 -0.0255 0.5311 1.0000
6.500 0.7636 0.03726 0.02617 -0.0204 0.5186 1.0000
6.750 0.7741 0.03770 0.02666 -0.0178 0.5083 1.0000
7.000 0.8018 0.03733 0.02633 -0.0170 0.5000 1.0000
7.250 0.7989 0.03849 0.02752 -0.0133 0.4875 1.0000
7.500 0.8168 0.03861 0.02767 -0.0115 0.4776 1.0000
7.750 0.8412 0.03835 0.02748 -0.0103 0.4681 1.0000
8.000 0.8417 0.03950 0.02867 -0.0073 0.4553 1.0000
8.250 0.8550 0.03996 0.02917 -0.0054 0.4442 1.0000
8.500 0.8891 0.03905 0.02830 -0.0049 0.4350 1.0000
8.750 0.8883 0.04044 0.02976 -0.0021 0.4218 1.0000
9.000 0.8950 0.04144 0.03081 0.0000 0.4093 1.0000
9.250 0.9136 0.04160 0.03100 0.0014 0.3982 1.0000
9.500 0.9400 0.04119 0.03062 0.0025 0.3873 1.0000
9.750 0.9409 0.04271 0.03221 0.0047 0.3743 1.0000
10.000 0.9478 0.04389 0.03343 0.0064 0.3620 1.0000
10.250 0.9631 0.04440 0.03396 0.0078 0.3504 1.0000
10.500 0.9874 0.04419 0.03373 0.0090 0.3391 1.0000
10.750 0.9859 0.04614 0.03577 0.0108 0.3267 1.0000
11.000 0.9899 0.04772 0.03740 0.0123 0.3150 1.0000
11.250 1.0024 0.04856 0.03825 0.0136 0.3039 1.0000
11.500 1.0193 0.04903 0.03870 0.0148 0.2929 1.0000
11.750 1.0138 0.05162 0.04141 0.0161 0.2819 1.0000
12.000 1.0213 0.05305 0.04287 0.0172 0.2717 1.0000
12.250 1.0386 0.05353 0.04332 0.0183 0.2617 1.0000
12.500 1.0286 0.05680 0.04675 0.0192 0.2521 1.0000
12.750 1.0409 0.05787 0.04782 0.0202 0.2432 1.0000
13.000 1.0386 0.06047 0.05052 0.0210 0.2342 1.0000
13.250 1.0398 0.06279 0.05293 0.0216 0.2259 1.0000
13.500 1.0456 0.06461 0.05479 0.0223 0.2177 1.0000
13.750 1.0389 0.06802 0.05834 0.0226 0.2105 1.0000
14.000 1.0420 0.07023 0.06061 0.0230 0.2029 1.0000
14.250 1.0340 0.07396 0.06446 0.0229 0.1962 1.0000
14.500 1.0241 0.07806 0.06868 0.0226 0.1895 1.0000
14.750 1.0310 0.07996 0.07061 0.0229 0.1833 1.0000
15.000 0.9790 0.09079 0.08169 0.0196 0.1777 1.0000
15.250 1.0329 0.08543 0.07623 0.0228 0.1709 1.0000
15.500 0.8910 0.11324 0.10429 0.0111 0.1642 1.0000
15.750 0.9017 0.11458 0.10570 0.0113 0.1591 1.0000
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Polar data table (+)
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