S2055 (s2055-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2055 (s2055-il) Reynolds number: 500,000 Max Cl/Cd: 71.77 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2055-il-500000-n5.txt Download as CSV file: xf-s2055-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5072 0.08307 0.08081 -0.0276 1.0000 0.0045
-9.000 -0.5105 0.07850 0.07627 -0.0294 1.0000 0.0042
-8.750 -0.5151 0.07440 0.07221 -0.0314 1.0000 0.0041
-8.500 -0.5425 0.06805 0.06593 -0.0355 1.0000 0.0042
-8.000 -0.5588 0.05937 0.05719 -0.0379 1.0000 0.0041
-7.500 -0.5686 0.04392 0.04132 -0.0420 0.9964 0.0041
-7.250 -0.5728 0.02645 0.02266 -0.0449 0.9889 0.0042
-7.000 -0.5527 0.02110 0.01653 -0.0456 0.9854 0.0045
-6.750 -0.5232 0.01966 0.01484 -0.0467 0.9837 0.0049
-6.500 -0.4947 0.01843 0.01340 -0.0475 0.9815 0.0052
-6.250 -0.4670 0.01778 0.01264 -0.0478 0.9781 0.0057
-6.000 -0.4384 0.01633 0.01092 -0.0483 0.9754 0.0061
-5.750 -0.4086 0.01483 0.00916 -0.0490 0.9732 0.0063
-5.500 -0.3778 0.01366 0.00779 -0.0498 0.9712 0.0067
-5.250 -0.3480 0.01274 0.00670 -0.0503 0.9688 0.0071
-5.000 -0.3221 0.01212 0.00598 -0.0500 0.9638 0.0076
-4.750 -0.2938 0.01124 0.00500 -0.0502 0.9600 0.0090
-4.500 -0.2631 0.01080 0.00452 -0.0509 0.9571 0.0105
-4.250 -0.2358 0.01056 0.00424 -0.0508 0.9521 0.0130
-4.000 -0.2085 0.01006 0.00368 -0.0508 0.9468 0.0161
-3.750 -0.1788 0.00975 0.00332 -0.0512 0.9430 0.0190
-3.500 -0.1525 0.00950 0.00302 -0.0508 0.9363 0.0216
-3.250 -0.1244 0.00918 0.00272 -0.0509 0.9308 0.0281
-3.000 -0.0973 0.00890 0.00246 -0.0507 0.9242 0.0411
-2.750 -0.0699 0.00863 0.00224 -0.0507 0.9174 0.0622
-2.500 -0.0427 0.00840 0.00204 -0.0505 0.9100 0.0824
-2.250 -0.0153 0.00815 0.00187 -0.0504 0.9023 0.1119
-2.000 0.0111 0.00787 0.00171 -0.0502 0.8929 0.1567
-1.750 0.0368 0.00744 0.00156 -0.0499 0.8827 0.2477
-1.500 0.0612 0.00686 0.00140 -0.0495 0.8698 0.3877
-1.250 0.0845 0.00627 0.00128 -0.0487 0.8540 0.5434
-1.000 0.1079 0.00588 0.00120 -0.0477 0.8360 0.6551
-0.750 0.1319 0.00569 0.00118 -0.0467 0.8172 0.7331
-0.500 0.1552 0.00558 0.00120 -0.0454 0.7988 0.8046
-0.250 0.1788 0.00556 0.00125 -0.0441 0.7829 0.8521
0.000 0.2035 0.00559 0.00127 -0.0431 0.7684 0.8786
0.250 0.2284 0.00563 0.00129 -0.0422 0.7545 0.8983
0.500 0.2534 0.00568 0.00131 -0.0413 0.7395 0.9137
0.750 0.2785 0.00575 0.00132 -0.0405 0.7234 0.9267
1.000 0.3041 0.00582 0.00134 -0.0398 0.7057 0.9389
1.250 0.3308 0.00590 0.00136 -0.0394 0.6839 0.9495
1.500 0.3586 0.00601 0.00139 -0.0393 0.6600 0.9588
1.750 0.3875 0.00616 0.00143 -0.0394 0.6275 0.9668
2.000 0.4175 0.00637 0.00147 -0.0400 0.5859 0.9728
2.250 0.4472 0.00664 0.00155 -0.0405 0.5352 0.9782
2.500 0.4759 0.00698 0.00167 -0.0409 0.4806 0.9834
2.750 0.5072 0.00732 0.00180 -0.0420 0.4293 0.9869
3.000 0.5375 0.00770 0.00196 -0.0428 0.3768 0.9910
3.250 0.5671 0.00812 0.00216 -0.0436 0.3197 0.9952
3.500 0.5975 0.00853 0.00234 -0.0446 0.2706 0.9995
3.750 0.6194 0.00880 0.00251 -0.0436 0.2442 1.0000
4.000 0.6408 0.00905 0.00268 -0.0424 0.2231 1.0000
4.250 0.6634 0.00928 0.00287 -0.0415 0.2069 1.0000
4.500 0.6861 0.00956 0.00310 -0.0406 0.1862 1.0000
4.750 0.7085 0.00993 0.00333 -0.0397 0.1541 1.0000
5.000 0.7305 0.01041 0.00361 -0.0389 0.1140 1.0000
5.250 0.7532 0.01086 0.00393 -0.0381 0.0850 1.0000
5.500 0.7762 0.01129 0.00427 -0.0374 0.0647 1.0000
5.750 0.7998 0.01168 0.00462 -0.0367 0.0512 1.0000
6.000 0.8235 0.01208 0.00502 -0.0361 0.0410 1.0000
6.250 0.8473 0.01249 0.00541 -0.0355 0.0326 1.0000
6.500 0.8712 0.01287 0.00583 -0.0349 0.0269 1.0000
6.750 0.8942 0.01340 0.00635 -0.0342 0.0210 1.0000
7.000 0.9179 0.01381 0.00682 -0.0336 0.0191 1.0000
7.250 0.9413 0.01427 0.00735 -0.0329 0.0175 1.0000
7.500 0.9641 0.01480 0.00792 -0.0322 0.0160 1.0000
7.750 0.9855 0.01549 0.00867 -0.0312 0.0139 1.0000
8.000 1.0083 0.01597 0.00925 -0.0306 0.0128 1.0000
8.250 1.0313 0.01641 0.00977 -0.0299 0.0116 1.0000
8.500 1.0536 0.01694 0.01037 -0.0292 0.0105 1.0000
8.750 1.0747 0.01759 0.01106 -0.0284 0.0093 1.0000
9.000 1.0935 0.01852 0.01210 -0.0271 0.0083 1.0000
9.250 1.1150 0.01908 0.01277 -0.0263 0.0075 1.0000
9.500 1.1358 0.01969 0.01346 -0.0254 0.0065 1.0000
9.750 1.1569 0.02022 0.01406 -0.0246 0.0054 1.0000
10.000 1.1743 0.02117 0.01509 -0.0233 0.0048 1.0000
10.250 1.1920 0.02204 0.01610 -0.0220 0.0043 1.0000
10.500 1.2085 0.02299 0.01718 -0.0206 0.0040 1.0000
10.750 1.2235 0.02402 0.01835 -0.0190 0.0037 1.0000
11.000 1.2379 0.02503 0.01949 -0.0174 0.0034 1.0000
11.250 1.2513 0.02601 0.02058 -0.0157 0.0031 1.0000
11.500 1.2596 0.02721 0.02192 -0.0132 0.0030 1.0000
11.750 1.2634 0.02868 0.02355 -0.0103 0.0028 1.0000
12.000 1.2620 0.03057 0.02564 -0.0071 0.0027 1.0000
12.250 1.2588 0.03263 0.02793 -0.0041 0.0026 1.0000
12.500 1.2573 0.03464 0.03012 -0.0017 0.0025 1.0000
12.750 1.2541 0.03691 0.03259 0.0003 0.0025 1.0000
13.000 1.2490 0.03949 0.03538 0.0019 0.0025 1.0000
13.250 1.2422 0.04248 0.03856 0.0029 0.0024 1.0000
13.500 1.2324 0.04606 0.04235 0.0031 0.0024 1.0000
13.750 1.2194 0.05044 0.04692 0.0024 0.0024 1.0000
14.000 1.2034 0.05585 0.05254 0.0005 0.0023 1.0000
14.250 1.1867 0.06217 0.05906 -0.0028 0.0023 1.0000
14.500 1.1675 0.06995 0.06703 -0.0077 0.0023 1.0000
14.750 1.1461 0.07916 0.07641 -0.0137 0.0024 1.0000
15.000 1.1204 0.08984 0.08725 -0.0204 0.0024 1.0000
15.250 1.0937 0.10078 0.09831 -0.0268 0.0025 1.0000
15.500 1.0677 0.11170 0.10933 -0.0330 0.0025 1.0000
15.750 1.0373 0.12389 0.12159 -0.0397 0.0026 1.0000
16.250 0.9749 0.15167 0.14960 -0.0542 0.0029 1.0000
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Polar data table (+)
Polar graphs
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