S2062 8% (s2062-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2062 8% (s2062-il) Reynolds number: 500,000 Max Cl/Cd: 74.6 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2062-il-500000-n5.txt Download as CSV file: xf-s2062-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2062 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4431 0.08191 0.07974 -0.0237 1.0000 0.0051
-9.750 -0.4522 0.07568 0.07354 -0.0257 1.0000 0.0052
-9.500 -0.4722 0.06707 0.06496 -0.0287 1.0000 0.0050
-9.250 -0.5380 0.04953 0.04750 -0.0359 1.0000 0.0046
-8.750 -0.6598 0.03983 0.03722 -0.0491 1.0000 0.0040
-8.500 -0.6735 0.03323 0.03011 -0.0489 1.0000 0.0041
-8.250 -0.6751 0.02865 0.02505 -0.0474 1.0000 0.0041
-8.000 -0.6698 0.02513 0.02108 -0.0456 1.0000 0.0043
-7.750 -0.6515 0.02264 0.01822 -0.0454 0.9990 0.0044
-7.500 -0.6233 0.02064 0.01592 -0.0468 0.9965 0.0046
-7.250 -0.5934 0.01912 0.01416 -0.0482 0.9943 0.0048
-7.000 -0.5651 0.01773 0.01254 -0.0489 0.9915 0.0050
-6.750 -0.5349 0.01689 0.01156 -0.0500 0.9888 0.0054
-6.500 -0.5039 0.01592 0.01042 -0.0511 0.9864 0.0058
-6.250 -0.4722 0.01492 0.00926 -0.0522 0.9844 0.0061
-6.000 -0.4416 0.01391 0.00806 -0.0531 0.9819 0.0063
-5.750 -0.4126 0.01303 0.00705 -0.0536 0.9780 0.0065
-5.500 -0.3814 0.01229 0.00619 -0.0545 0.9749 0.0067
-5.250 -0.3491 0.01168 0.00548 -0.0556 0.9723 0.0069
-5.000 -0.3166 0.01093 0.00460 -0.0567 0.9699 0.0078
-4.750 -0.2890 0.01049 0.00407 -0.0567 0.9641 0.0087
-4.500 -0.2582 0.01010 0.00362 -0.0573 0.9598 0.0101
-4.250 -0.2262 0.00969 0.00320 -0.0583 0.9563 0.0161
-4.000 -0.1989 0.00927 0.00288 -0.0582 0.9494 0.0357
-3.750 -0.1684 0.00896 0.00262 -0.0588 0.9441 0.0531
-3.500 -0.1397 0.00869 0.00239 -0.0591 0.9373 0.0716
-3.250 -0.1108 0.00839 0.00219 -0.0594 0.9303 0.0998
-3.000 -0.0830 0.00810 0.00202 -0.0594 0.9222 0.1322
-2.500 -0.0273 0.00767 0.00170 -0.0594 0.9049 0.1907
-2.250 0.0001 0.00744 0.00157 -0.0593 0.8957 0.2297
-2.000 0.0273 0.00725 0.00145 -0.0591 0.8856 0.2681
-1.750 0.0541 0.00703 0.00135 -0.0589 0.8742 0.3178
-1.500 0.0808 0.00681 0.00126 -0.0587 0.8623 0.3703
-1.250 0.1074 0.00659 0.00119 -0.0584 0.8502 0.4309
-1.000 0.1338 0.00637 0.00114 -0.0581 0.8372 0.4976
-0.750 0.1598 0.00613 0.00110 -0.0577 0.8227 0.5728
-0.500 0.1853 0.00591 0.00109 -0.0571 0.8070 0.6515
-0.250 0.2106 0.00578 0.00110 -0.0564 0.7898 0.7182
0.000 0.2361 0.00572 0.00112 -0.0557 0.7713 0.7645
0.250 0.2616 0.00571 0.00113 -0.0549 0.7509 0.7988
0.500 0.2868 0.00574 0.00115 -0.0541 0.7290 0.8272
0.750 0.3115 0.00578 0.00118 -0.0532 0.7049 0.8539
1.000 0.3359 0.00584 0.00121 -0.0522 0.6793 0.8800
1.250 0.3600 0.00592 0.00125 -0.0512 0.6520 0.9046
1.500 0.3847 0.00604 0.00129 -0.0503 0.6225 0.9292
1.750 0.4133 0.00618 0.00134 -0.0503 0.5896 0.9554
2.000 0.4478 0.00638 0.00140 -0.0517 0.5506 0.9806
2.250 0.4801 0.00661 0.00149 -0.0529 0.5103 1.0000
2.500 0.5048 0.00688 0.00159 -0.0523 0.4712 1.0000
2.750 0.5299 0.00715 0.00172 -0.0518 0.4353 1.0000
3.000 0.5550 0.00744 0.00188 -0.0514 0.3979 1.0000
3.250 0.5785 0.00792 0.00207 -0.0507 0.3322 1.0000
3.500 0.6012 0.00855 0.00231 -0.0500 0.2512 1.0000
3.750 0.6248 0.00911 0.00256 -0.0495 0.1881 1.0000
4.000 0.6494 0.00955 0.00281 -0.0491 0.1464 1.0000
4.250 0.6743 0.00996 0.00310 -0.0487 0.1132 1.0000
4.500 0.6984 0.01049 0.00343 -0.0482 0.0730 1.0000
4.750 0.7226 0.01102 0.00380 -0.0477 0.0411 1.0000
5.000 0.7468 0.01156 0.00421 -0.0471 0.0196 1.0000
5.250 0.7722 0.01193 0.00459 -0.0467 0.0158 1.0000
5.500 0.7977 0.01228 0.00502 -0.0463 0.0148 1.0000
5.750 0.8229 0.01267 0.00546 -0.0459 0.0139 1.0000
6.000 0.8478 0.01309 0.00594 -0.0454 0.0130 1.0000
6.250 0.8723 0.01356 0.00646 -0.0449 0.0123 1.0000
6.500 0.8963 0.01411 0.00707 -0.0443 0.0118 1.0000
6.750 0.9196 0.01474 0.00778 -0.0435 0.0113 1.0000
7.000 0.9416 0.01554 0.00870 -0.0427 0.0108 1.0000
7.250 0.9614 0.01667 0.00995 -0.0414 0.0103 1.0000
7.500 0.9838 0.01739 0.01076 -0.0406 0.0102 1.0000
7.750 1.0056 0.01819 0.01165 -0.0397 0.0100 1.0000
8.000 1.0274 0.01899 0.01255 -0.0389 0.0097 1.0000
8.250 1.0490 0.01978 0.01344 -0.0380 0.0093 1.0000
8.500 1.0700 0.02066 0.01446 -0.0371 0.0089 1.0000
8.750 1.0899 0.02174 0.01566 -0.0360 0.0086 1.0000
9.000 1.1092 0.02287 0.01693 -0.0349 0.0083 1.0000
9.250 1.1279 0.02408 0.01829 -0.0338 0.0080 1.0000
9.500 1.1459 0.02530 0.01966 -0.0326 0.0077 1.0000
9.750 1.1636 0.02636 0.02083 -0.0315 0.0074 1.0000
10.000 1.1805 0.02735 0.02192 -0.0303 0.0071 1.0000
10.250 1.1946 0.02870 0.02340 -0.0289 0.0068 1.0000
10.500 1.1968 0.03187 0.02686 -0.0263 0.0063 1.0000
10.750 1.2083 0.03314 0.02833 -0.0245 0.0062 1.0000
11.000 1.2158 0.03458 0.02996 -0.0223 0.0061 1.0000
11.250 1.2178 0.03623 0.03182 -0.0194 0.0059 1.0000
11.500 1.2147 0.03836 0.03416 -0.0164 0.0058 1.0000
11.750 1.2101 0.04065 0.03667 -0.0139 0.0056 1.0000
12.000 1.2031 0.04332 0.03956 -0.0120 0.0055 1.0000
12.250 1.1912 0.04676 0.04321 -0.0107 0.0054 1.0000
12.500 1.1782 0.05067 0.04734 -0.0105 0.0053 1.0000
12.750 1.1634 0.05531 0.05219 -0.0115 0.0052 1.0000
13.000 1.1458 0.06107 0.05815 -0.0140 0.0052 1.0000
13.250 1.1268 0.06797 0.06524 -0.0181 0.0052 1.0000
13.500 1.1035 0.07680 0.07426 -0.0240 0.0053 1.0000
13.750 1.0826 0.08630 0.08392 -0.0306 0.0053 1.0000
14.000 1.0550 0.09830 0.09607 -0.0385 0.0055 1.0000
14.250 1.0222 0.11250 0.11039 -0.0472 0.0057 1.0000
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Polar data table (+)
Polar graphs
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