SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD2083 (9.0%) (sd2083-il) Reynolds number: 500,000 Max Cl/Cd: 108.95 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd2083-il-500000.txt Download as CSV file: xf-sd2083-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SD2083 (9.0%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3889 0.08432 0.08215 -0.0404 1.0000 0.0191
-8.500 -0.3925 0.08021 0.07809 -0.0424 1.0000 0.0191
-8.250 -0.4035 0.07754 0.07550 -0.0420 1.0000 0.0191
-8.000 -0.4123 0.06892 0.06693 -0.0516 0.9917 0.0195
-7.750 -0.3969 0.06389 0.06185 -0.0582 0.9867 0.0203
-7.500 -0.3733 0.05867 0.05656 -0.0661 0.9835 0.0209
-7.250 -0.3528 0.05377 0.05156 -0.0723 0.9766 0.0218
-7.000 -0.3299 0.04790 0.04551 -0.0789 0.9710 0.0233
-6.750 -0.3130 0.04232 0.03964 -0.0820 0.9609 0.0254
-6.500 -0.3062 0.03615 0.03285 -0.0823 0.9494 0.0273
-6.250 -0.2944 0.03278 0.02938 -0.0820 0.9425 0.0284
-6.000 -0.2769 0.03138 0.02792 -0.0813 0.9352 0.0295
-5.750 -0.2587 0.02985 0.02624 -0.0804 0.9294 0.0315
-5.500 -0.2312 0.03082 0.02688 -0.0790 0.9229 0.0363
-5.250 -0.2236 0.02472 0.02028 -0.0778 0.9162 0.0384
-5.000 -0.2030 0.01934 0.01431 -0.0755 0.9102 0.0249
-4.750 -0.1819 0.01533 0.00966 -0.0735 0.9047 0.0210
-4.500 -0.1574 0.01407 0.00819 -0.0725 0.9004 0.0208
-4.250 -0.1323 0.01311 0.00711 -0.0719 0.8948 0.0210
-4.000 -0.1073 0.01236 0.00627 -0.0712 0.8899 0.0215
-3.750 -0.0820 0.01180 0.00564 -0.0706 0.8856 0.0226
-3.500 -0.0567 0.01115 0.00491 -0.0700 0.8799 0.0228
-3.250 -0.0312 0.01060 0.00428 -0.0693 0.8752 0.0233
-3.000 -0.0054 0.01017 0.00379 -0.0688 0.8704 0.0244
-2.750 0.0210 0.00983 0.00337 -0.0684 0.8648 0.0259
-2.500 0.0474 0.00948 0.00293 -0.0679 0.8601 0.0288
-2.250 0.0740 0.00919 0.00266 -0.0675 0.8548 0.0391
-2.000 0.0990 0.00858 0.00242 -0.0671 0.8490 0.1365
-1.750 0.1239 0.00805 0.00226 -0.0667 0.8442 0.2566
-1.500 0.1481 0.00748 0.00218 -0.0663 0.8376 0.4067
-1.250 0.1718 0.00698 0.00210 -0.0655 0.8318 0.5485
-1.000 0.1928 0.00641 0.00210 -0.0640 0.8252 0.7145
-0.750 0.2173 0.00588 0.00215 -0.0624 0.8190 0.9133
-0.500 0.2664 0.00586 0.00208 -0.0666 0.8138 0.9681
-0.250 0.3225 0.00584 0.00199 -0.0726 0.8071 0.9916
0.000 0.3661 0.00581 0.00187 -0.0760 0.8005 1.0000
0.250 0.3904 0.00581 0.00181 -0.0752 0.7914 1.0000
0.500 0.4149 0.00582 0.00176 -0.0745 0.7826 1.0000
0.750 0.4396 0.00583 0.00170 -0.0737 0.7737 1.0000
1.000 0.4645 0.00585 0.00169 -0.0731 0.7638 1.0000
1.250 0.4895 0.00589 0.00167 -0.0725 0.7545 1.0000
1.500 0.5146 0.00593 0.00166 -0.0718 0.7451 1.0000
1.750 0.5399 0.00597 0.00168 -0.0712 0.7343 1.0000
2.000 0.5651 0.00602 0.00170 -0.0707 0.7232 1.0000
2.250 0.5904 0.00608 0.00173 -0.0701 0.7113 1.0000
2.500 0.6155 0.00616 0.00178 -0.0695 0.6983 1.0000
2.750 0.6406 0.00624 0.00182 -0.0688 0.6834 1.0000
3.000 0.6655 0.00634 0.00188 -0.0682 0.6668 1.0000
3.250 0.6902 0.00646 0.00194 -0.0675 0.6480 1.0000
3.500 0.7147 0.00660 0.00204 -0.0667 0.6262 1.0000
3.750 0.7387 0.00678 0.00214 -0.0659 0.6009 1.0000
4.000 0.7623 0.00700 0.00227 -0.0651 0.5714 1.0000
4.250 0.7854 0.00727 0.00242 -0.0642 0.5370 1.0000
4.500 0.8078 0.00761 0.00262 -0.0632 0.4971 1.0000
4.750 0.8295 0.00802 0.00285 -0.0621 0.4522 1.0000
5.000 0.8506 0.00850 0.00313 -0.0610 0.4063 1.0000
5.250 0.8717 0.00900 0.00343 -0.0599 0.3597 1.0000
5.500 0.8930 0.00950 0.00375 -0.0589 0.3184 1.0000
5.750 0.9131 0.01010 0.00413 -0.0578 0.2684 1.0000
6.000 0.9342 0.01063 0.00448 -0.0568 0.2303 1.0000
6.250 0.9560 0.01111 0.00484 -0.0559 0.2005 1.0000
6.500 0.9771 0.01164 0.00523 -0.0549 0.1689 1.0000
6.750 0.9977 0.01221 0.00566 -0.0539 0.1367 1.0000
7.000 1.0168 0.01292 0.00615 -0.0527 0.0999 1.0000
7.250 1.0359 0.01362 0.00669 -0.0515 0.0688 1.0000
7.500 1.0503 0.01477 0.00752 -0.0495 0.0260 1.0000
7.750 1.0671 0.01571 0.00841 -0.0478 0.0146 1.0000
8.000 1.0867 0.01635 0.00912 -0.0465 0.0129 1.0000
8.250 1.1045 0.01713 0.00999 -0.0449 0.0116 1.0000
8.500 1.1182 0.01824 0.01121 -0.0427 0.0107 1.0000
8.750 1.1319 0.01925 0.01234 -0.0406 0.0104 1.0000
9.000 1.1468 0.02010 0.01328 -0.0387 0.0101 1.0000
9.250 1.1588 0.02102 0.01428 -0.0363 0.0098 1.0000
9.500 1.1707 0.02185 0.01520 -0.0340 0.0092 1.0000
9.750 1.1807 0.02286 0.01629 -0.0315 0.0089 1.0000
10.000 1.1882 0.02417 0.01773 -0.0288 0.0089 1.0000
10.250 1.1974 0.02540 0.01907 -0.0264 0.0087 1.0000
10.500 1.2066 0.02666 0.02042 -0.0243 0.0084 1.0000
10.750 1.2144 0.02822 0.02211 -0.0221 0.0083 1.0000
11.000 1.2224 0.02974 0.02374 -0.0201 0.0081 1.0000
11.250 1.2298 0.03149 0.02562 -0.0182 0.0081 1.0000
11.500 1.2359 0.03340 0.02768 -0.0162 0.0080 1.0000
11.750 1.2396 0.03568 0.03008 -0.0143 0.0077 1.0000
12.000 1.2434 0.03794 0.03253 -0.0126 0.0077 1.0000
12.250 1.2450 0.04042 0.03522 -0.0108 0.0077 1.0000
12.500 1.2422 0.04347 0.03845 -0.0091 0.0076 1.0000
12.750 1.2382 0.04648 0.04175 -0.0076 0.0078 1.0000
13.000 1.2260 0.05092 0.04653 -0.0062 0.0082 1.0000
13.250 1.1969 0.05757 0.05364 -0.0054 0.0087 1.0000
13.500 1.1736 0.06361 0.05997 -0.0060 0.0089 1.0000
13.750 1.1551 0.06927 0.06584 -0.0075 0.0092 1.0000
14.000 1.1335 0.07590 0.07267 -0.0100 0.0093 1.0000
14.250 1.1129 0.08299 0.07995 -0.0135 0.0095 1.0000
14.500 1.0942 0.09040 0.08752 -0.0178 0.0095 1.0000
14.750 1.0736 0.09899 0.09627 -0.0231 0.0096 1.0000
15.000 1.0537 0.10825 0.10568 -0.0291 0.0096 1.0000
15.250 1.0321 0.11876 0.11633 -0.0359 0.0096 1.0000
15.500 1.0129 0.12928 0.12696 -0.0426 0.0097 1.0000
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Polar data table (+)
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