S2055 (s2055-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2055 (s2055-il) Reynolds number: 200,000 Max Cl/Cd: 61.94 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2055-il-200000-n5.txt Download as CSV file: xf-s2055-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4811 0.08793 0.08435 -0.0269 1.0000 0.0124
-8.750 -0.4835 0.08379 0.08025 -0.0288 1.0000 0.0123
-8.500 -0.4895 0.07889 0.07542 -0.0314 1.0000 0.0127
-8.250 -0.4966 0.07497 0.07156 -0.0333 1.0000 0.0125
-8.000 -0.5093 0.07092 0.06756 -0.0353 1.0000 0.0123
-7.750 -0.5168 0.06630 0.06294 -0.0371 1.0000 0.0122
-7.500 -0.5226 0.06201 0.05860 -0.0379 1.0000 0.0120
-7.250 -0.5269 0.05772 0.05424 -0.0378 1.0000 0.0118
-7.000 -0.5309 0.05305 0.04944 -0.0371 1.0000 0.0117
-6.750 -0.5323 0.04851 0.04472 -0.0358 1.0000 0.0115
-6.500 -0.5311 0.04408 0.04006 -0.0342 1.0000 0.0113
-6.250 -0.5279 0.03950 0.03518 -0.0322 1.0000 0.0112
-6.000 -0.5114 0.03376 0.02893 -0.0325 0.9974 0.0111
-5.750 -0.4856 0.02845 0.02294 -0.0337 0.9937 0.0110
-5.500 -0.4590 0.02448 0.01831 -0.0341 0.9897 0.0113
-5.250 -0.4295 0.02166 0.01489 -0.0346 0.9864 0.0118
-5.000 -0.3980 0.01957 0.01236 -0.0354 0.9838 0.0126
-4.750 -0.3682 0.01810 0.01062 -0.0360 0.9805 0.0141
-4.500 -0.3388 0.01718 0.00964 -0.0367 0.9763 0.0163
-4.250 -0.3073 0.01605 0.00835 -0.0375 0.9730 0.0185
-4.000 -0.2744 0.01503 0.00719 -0.0386 0.9704 0.0209
-3.750 -0.2462 0.01437 0.00648 -0.0389 0.9654 0.0267
-3.500 -0.2154 0.01370 0.00572 -0.0396 0.9611 0.0319
-3.250 -0.1818 0.01324 0.00522 -0.0410 0.9580 0.0412
-3.000 -0.1502 0.01268 0.00469 -0.0419 0.9541 0.0588
-2.750 -0.1212 0.01226 0.00435 -0.0423 0.9485 0.0884
-2.500 -0.0886 0.01177 0.00403 -0.0436 0.9449 0.1423
-2.250 -0.0602 0.01089 0.00380 -0.0444 0.9404 0.2964
-2.000 -0.0374 0.00992 0.00363 -0.0438 0.9336 0.5055
-1.750 -0.0122 0.00919 0.00363 -0.0429 0.9294 0.6962
-1.500 0.0107 0.00901 0.00368 -0.0412 0.9220 0.7890
-1.250 0.0396 0.00894 0.00365 -0.0407 0.9170 0.8460
-1.000 0.0667 0.00893 0.00365 -0.0398 0.9102 0.8903
-0.750 0.0996 0.00893 0.00363 -0.0401 0.9043 0.9257
-0.500 0.1397 0.00891 0.00354 -0.0421 0.8977 0.9488
-0.250 0.1828 0.00883 0.00339 -0.0449 0.8888 0.9624
0.000 0.2246 0.00872 0.00320 -0.0475 0.8753 0.9721
0.250 0.2673 0.00861 0.00301 -0.0503 0.8601 0.9788
0.500 0.3060 0.00853 0.00286 -0.0524 0.8446 0.9849
0.750 0.3439 0.00847 0.00274 -0.0545 0.8292 0.9903
1.000 0.3797 0.00843 0.00265 -0.0561 0.8137 0.9957
1.250 0.4133 0.00841 0.00259 -0.0574 0.7965 1.0000
1.500 0.4359 0.00843 0.00256 -0.0562 0.7790 1.0000
1.750 0.4580 0.00847 0.00255 -0.0550 0.7591 1.0000
2.000 0.4800 0.00854 0.00256 -0.0537 0.7377 1.0000
2.250 0.5017 0.00862 0.00261 -0.0524 0.7132 1.0000
2.500 0.5232 0.00874 0.00265 -0.0510 0.6841 1.0000
2.750 0.5442 0.00889 0.00270 -0.0495 0.6490 1.0000
3.000 0.5643 0.00911 0.00277 -0.0478 0.6048 1.0000
3.250 0.5831 0.00943 0.00290 -0.0459 0.5502 1.0000
3.500 0.6010 0.00986 0.00306 -0.0439 0.4908 1.0000
3.750 0.6187 0.01036 0.00328 -0.0420 0.4299 1.0000
4.000 0.6368 0.01092 0.00356 -0.0403 0.3703 1.0000
4.250 0.6562 0.01145 0.00386 -0.0389 0.3201 1.0000
4.500 0.6774 0.01190 0.00420 -0.0378 0.2836 1.0000
4.750 0.6993 0.01232 0.00453 -0.0369 0.2542 1.0000
5.000 0.7217 0.01274 0.00487 -0.0360 0.2271 1.0000
5.250 0.7444 0.01314 0.00524 -0.0352 0.2028 1.0000
5.500 0.7665 0.01364 0.00563 -0.0344 0.1712 1.0000
5.750 0.7880 0.01423 0.00605 -0.0335 0.1303 1.0000
6.000 0.8085 0.01497 0.00662 -0.0325 0.0895 1.0000
6.250 0.8293 0.01572 0.00725 -0.0315 0.0640 1.0000
6.500 0.8508 0.01640 0.00791 -0.0306 0.0500 1.0000
6.750 0.8719 0.01715 0.00867 -0.0296 0.0406 1.0000
7.000 0.8934 0.01784 0.00947 -0.0287 0.0346 1.0000
7.250 0.9123 0.01885 0.01053 -0.0273 0.0303 1.0000
7.500 0.9328 0.01964 0.01147 -0.0262 0.0277 1.0000
7.750 0.9534 0.02042 0.01235 -0.0252 0.0247 1.0000
8.000 0.9722 0.02141 0.01342 -0.0239 0.0225 1.0000
8.250 0.9870 0.02305 0.01521 -0.0221 0.0207 1.0000
8.500 1.0071 0.02396 0.01631 -0.0211 0.0193 1.0000
8.750 1.0266 0.02486 0.01738 -0.0200 0.0170 1.0000
9.000 1.0441 0.02604 0.01869 -0.0187 0.0155 1.0000
9.250 1.0582 0.02760 0.02035 -0.0172 0.0139 1.0000
9.500 1.0742 0.02899 0.02197 -0.0158 0.0125 1.0000
9.750 1.0888 0.03055 0.02378 -0.0142 0.0111 1.0000
10.000 1.1008 0.03233 0.02580 -0.0124 0.0104 1.0000
10.250 1.1108 0.03398 0.02768 -0.0105 0.0096 1.0000
10.500 1.1171 0.03580 0.02970 -0.0083 0.0092 1.0000
10.750 1.1172 0.03805 0.03215 -0.0054 0.0088 1.0000
11.000 1.1097 0.04123 0.03562 -0.0023 0.0085 1.0000
11.250 1.1016 0.04424 0.03894 0.0004 0.0083 1.0000
11.500 1.0924 0.04734 0.04233 0.0025 0.0082 1.0000
11.750 1.0800 0.05092 0.04619 0.0038 0.0081 1.0000
12.000 1.0646 0.05514 0.05068 0.0040 0.0080 1.0000
12.250 1.0489 0.05984 0.05561 0.0030 0.0081 1.0000
12.500 1.0314 0.06547 0.06145 0.0005 0.0080 1.0000
12.750 1.0128 0.07216 0.06833 -0.0034 0.0081 1.0000
13.000 0.9943 0.07992 0.07627 -0.0088 0.0082 1.0000
13.250 0.9748 0.08907 0.08556 -0.0153 0.0083 1.0000
13.500 0.9546 0.09900 0.09560 -0.0219 0.0084 1.0000
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Polar data table (+)
Polar graphs
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