S5010 (s5010-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S5010 (s5010-il) Reynolds number: 100,000 Max Cl/Cd: 47.68 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s5010-il-100000-n5.txt Download as CSV file: xf-s5010-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S5010
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5536 0.12056 0.11610 0.0202 1.0000 0.0513
-9.750 -0.5552 0.11649 0.11210 0.0161 1.0000 0.0516
-9.500 -0.5551 0.11216 0.10781 0.0125 1.0000 0.0517
-9.250 -0.5552 0.10763 0.10334 0.0088 1.0000 0.0518
-9.000 -0.5557 0.10282 0.09859 0.0048 1.0000 0.0519
-8.500 -0.5405 0.08825 0.08401 0.0044 1.0000 0.0294
-8.250 -0.5384 0.08416 0.07998 0.0024 1.0000 0.0288
-8.000 -0.5403 0.07932 0.07520 -0.0014 1.0000 0.0281
-7.750 -0.5423 0.07399 0.06989 -0.0058 1.0000 0.0275
-7.500 -0.5416 0.06825 0.06410 -0.0100 1.0000 0.0267
-7.250 -0.5395 0.06223 0.05797 -0.0137 1.0000 0.0260
-7.000 -0.5351 0.05607 0.05161 -0.0167 1.0000 0.0253
-6.750 -0.5274 0.05004 0.04526 -0.0187 1.0000 0.0247
-6.500 -0.5155 0.04467 0.03951 -0.0200 1.0000 0.0245
-6.250 -0.4928 0.04054 0.03494 -0.0219 0.9363 0.0254
-6.000 -0.4726 0.03720 0.03107 -0.0221 0.9090 0.0271
-5.750 -0.4547 0.03402 0.02731 -0.0211 0.8886 0.0281
-5.500 -0.4358 0.03119 0.02392 -0.0197 0.8722 0.0284
-5.250 -0.4150 0.02875 0.02090 -0.0183 0.8578 0.0290
-5.000 -0.3921 0.02683 0.01846 -0.0170 0.8445 0.0299
-4.750 -0.3698 0.02506 0.01652 -0.0162 0.8320 0.0322
-4.500 -0.3456 0.02384 0.01509 -0.0154 0.8202 0.0345
-4.250 -0.3206 0.02246 0.01346 -0.0144 0.8094 0.0358
-4.000 -0.2957 0.02127 0.01204 -0.0134 0.7993 0.0374
-3.750 -0.2697 0.02043 0.01099 -0.0126 0.7883 0.0400
-3.500 -0.2457 0.01936 0.00994 -0.0119 0.7782 0.0437
-3.250 -0.2215 0.01860 0.00907 -0.0108 0.7690 0.0464
-3.000 -0.1965 0.01794 0.00827 -0.0100 0.7588 0.0499
-2.500 -0.1469 0.01673 0.00691 -0.0084 0.7406 0.0687
-2.250 -0.1220 0.01592 0.00633 -0.0078 0.7307 0.1173
-2.000 -0.0991 0.01485 0.00594 -0.0071 0.7217 0.2797
-1.750 -0.0801 0.01347 0.00580 -0.0054 0.7134 0.5781
-1.500 -0.0249 0.01268 0.00595 -0.0080 0.7036 0.9104
-1.250 0.0323 0.01273 0.00572 -0.0130 0.6940 0.9743
-1.000 0.0821 0.01267 0.00536 -0.0174 0.6842 1.0000
-0.750 0.1062 0.01268 0.00520 -0.0168 0.6741 1.0000
-0.500 0.1301 0.01271 0.00504 -0.0161 0.6649 1.0000
-0.250 0.1543 0.01275 0.00489 -0.0153 0.6555 1.0000
0.000 0.1791 0.01281 0.00481 -0.0148 0.6455 1.0000
0.250 0.2036 0.01287 0.00472 -0.0141 0.6364 1.0000
0.500 0.2284 0.01294 0.00465 -0.0134 0.6267 1.0000
0.750 0.2536 0.01302 0.00464 -0.0129 0.6164 1.0000
1.000 0.2786 0.01310 0.00460 -0.0123 0.6068 1.0000
1.250 0.3037 0.01319 0.00459 -0.0116 0.5970 1.0000
1.500 0.3292 0.01330 0.00462 -0.0111 0.5861 1.0000
1.750 0.3546 0.01340 0.00465 -0.0106 0.5759 1.0000
2.000 0.3798 0.01351 0.00466 -0.0099 0.5661 1.0000
2.250 0.4054 0.01363 0.00475 -0.0094 0.5547 1.0000
2.500 0.4310 0.01377 0.00484 -0.0090 0.5434 1.0000
2.750 0.4566 0.01390 0.00493 -0.0084 0.5322 1.0000
3.000 0.4820 0.01404 0.00503 -0.0079 0.5211 1.0000
3.250 0.5076 0.01419 0.00513 -0.0074 0.5096 1.0000
3.500 0.5333 0.01436 0.00529 -0.0069 0.4969 1.0000
3.750 0.5590 0.01453 0.00545 -0.0065 0.4841 1.0000
4.000 0.5846 0.01472 0.00565 -0.0060 0.4711 1.0000
4.250 0.6102 0.01491 0.00584 -0.0056 0.4578 1.0000
4.500 0.6358 0.01512 0.00605 -0.0052 0.4440 1.0000
4.750 0.6612 0.01535 0.00627 -0.0047 0.4298 1.0000
5.000 0.6867 0.01559 0.00655 -0.0043 0.4150 1.0000
5.250 0.7119 0.01586 0.00682 -0.0039 0.3997 1.0000
5.500 0.7371 0.01615 0.00711 -0.0035 0.3839 1.0000
5.750 0.7620 0.01646 0.00746 -0.0031 0.3680 1.0000
6.000 0.7868 0.01681 0.00780 -0.0027 0.3519 1.0000
6.250 0.8114 0.01718 0.00820 -0.0023 0.3353 1.0000
6.500 0.8358 0.01759 0.00865 -0.0019 0.3182 1.0000
6.750 0.8599 0.01804 0.00912 -0.0015 0.3014 1.0000
7.000 0.8836 0.01853 0.00966 -0.0011 0.2845 1.0000
7.250 0.9069 0.01906 0.01021 -0.0007 0.2682 1.0000
7.500 0.9297 0.01965 0.01080 -0.0002 0.2519 1.0000
7.750 0.9523 0.02026 0.01146 0.0002 0.2360 1.0000
8.000 0.9743 0.02092 0.01221 0.0007 0.2200 1.0000
8.250 0.9957 0.02162 0.01297 0.0012 0.2049 1.0000
8.500 1.0165 0.02238 0.01378 0.0017 0.1902 1.0000
8.750 1.0365 0.02319 0.01465 0.0023 0.1762 1.0000
9.000 1.0556 0.02406 0.01558 0.0029 0.1630 1.0000
9.250 1.0737 0.02500 0.01658 0.0036 0.1508 1.0000
9.500 1.0905 0.02602 0.01767 0.0043 0.1398 1.0000
9.750 1.1064 0.02707 0.01882 0.0051 0.1286 1.0000
10.000 1.1213 0.02819 0.02005 0.0060 0.1182 1.0000
10.250 1.1341 0.02942 0.02137 0.0069 0.1094 1.0000
10.500 1.1436 0.03081 0.02279 0.0080 0.1016 1.0000
10.750 1.1535 0.03216 0.02431 0.0090 0.0937 1.0000
11.000 1.1552 0.03382 0.02597 0.0105 0.0885 1.0000
11.250 1.1604 0.03548 0.02785 0.0115 0.0823 1.0000
11.500 1.1612 0.03752 0.02993 0.0121 0.0773 1.0000
11.750 1.1639 0.03965 0.03221 0.0125 0.0723 1.0000
12.000 1.1651 0.04198 0.03468 0.0127 0.0678 1.0000
12.250 1.1626 0.04474 0.03741 0.0125 0.0641 1.0000
12.500 1.1633 0.04742 0.04035 0.0122 0.0597 1.0000
12.750 1.1608 0.05050 0.04354 0.0116 0.0560 1.0000
13.000 1.1549 0.05400 0.04705 0.0106 0.0530 1.0000
13.250 1.1515 0.05754 0.05082 0.0095 0.0496 1.0000
13.500 1.1450 0.06154 0.05498 0.0080 0.0463 1.0000
13.750 1.1369 0.06588 0.05940 0.0061 0.0440 1.0000
14.000 1.1274 0.07053 0.06410 0.0041 0.0417 1.0000
14.250 1.1184 0.07547 0.06927 0.0018 0.0394 1.0000
14.500 1.1085 0.08077 0.07472 -0.0008 0.0373 1.0000
14.750 1.0977 0.08642 0.08049 -0.0037 0.0356 1.0000
15.000 1.0866 0.09229 0.08645 -0.0068 0.0342 1.0000
15.250 1.0762 0.09806 0.09222 -0.0097 0.0328 1.0000
15.500 1.0630 0.10493 0.09932 -0.0133 0.0316 1.0000
15.750 1.0497 0.11196 0.10652 -0.0169 0.0306 1.0000
16.000 1.0356 0.11941 0.11413 -0.0208 0.0298 1.0000
16.250 1.0208 0.12726 0.12214 -0.0250 0.0293 1.0000
16.500 1.0022 0.13641 0.13144 -0.0300 0.0290 1.0000
16.750 0.9726 0.14918 0.14435 -0.0368 0.0298 1.0000
17.000 0.9339 0.16607 0.16123 -0.0455 0.0311 1.0000
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