S2055 (s2055-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2055 (s2055-il) Reynolds number: 100,000 Max Cl/Cd: 48.79 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2055-il-100000-n5.txt Download as CSV file: xf-s2055-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4775 0.08901 0.08403 -0.0274 1.0000 0.0240
-8.500 -0.4831 0.08413 0.07923 -0.0299 1.0000 0.0229
-8.250 -0.5003 0.07639 0.07162 -0.0369 1.0000 0.0209
-8.000 -0.5033 0.07221 0.06740 -0.0387 1.0000 0.0204
-7.750 -0.5084 0.06844 0.06363 -0.0389 1.0000 0.0201
-7.500 -0.5127 0.06454 0.05970 -0.0391 1.0000 0.0198
-7.250 -0.5155 0.06063 0.05573 -0.0390 1.0000 0.0196
-7.000 -0.5175 0.05649 0.05147 -0.0385 1.0000 0.0194
-6.750 -0.5173 0.05244 0.04726 -0.0376 1.0000 0.0192
-6.500 -0.5149 0.04847 0.04308 -0.0363 1.0000 0.0191
-6.250 -0.5105 0.04450 0.03883 -0.0348 1.0000 0.0190
-6.000 -0.5037 0.04058 0.03455 -0.0332 1.0000 0.0190
-5.750 -0.4938 0.03696 0.03049 -0.0314 1.0000 0.0193
-5.250 -0.4672 0.03085 0.02341 -0.0281 1.0000 0.0217
-5.000 -0.4505 0.02884 0.02112 -0.0268 1.0000 0.0230
-4.750 -0.4316 0.02657 0.01843 -0.0253 1.0000 0.0237
-4.500 -0.4112 0.02456 0.01606 -0.0239 1.0000 0.0247
-4.250 -0.3897 0.02277 0.01393 -0.0226 1.0000 0.0263
-4.000 -0.3678 0.02151 0.01238 -0.0213 1.0000 0.0291
-3.750 -0.3472 0.02030 0.01113 -0.0203 1.0000 0.0341
-3.500 -0.3171 0.01911 0.00978 -0.0208 0.9972 0.0387
-3.250 -0.2846 0.01825 0.00882 -0.0220 0.9932 0.0478
-3.000 -0.2530 0.01735 0.00781 -0.0229 0.9887 0.0569
-2.750 -0.2200 0.01660 0.00705 -0.0242 0.9844 0.0765
-2.500 -0.1888 0.01587 0.00657 -0.0253 0.9798 0.1300
-2.250 -0.1603 0.01474 0.00628 -0.0263 0.9749 0.3027
-2.000 -0.1365 0.01336 0.00631 -0.0255 0.9709 0.6425
-1.750 -0.1122 0.01318 0.00658 -0.0232 0.9658 0.8371
-1.500 -0.0711 0.01329 0.00660 -0.0249 0.9629 0.9275
-1.250 0.0094 0.01337 0.00641 -0.0352 0.9695 0.9948
-1.000 0.0434 0.01338 0.00625 -0.0369 0.9622 1.0000
-0.750 0.0810 0.01343 0.00615 -0.0393 0.9567 1.0000
-0.500 0.1111 0.01344 0.00604 -0.0401 0.9477 1.0000
-0.250 0.1510 0.01346 0.00594 -0.0428 0.9424 1.0000
0.250 0.2171 0.01339 0.00574 -0.0452 0.9232 1.0000
0.500 0.2576 0.01325 0.00556 -0.0476 0.9144 1.0000
0.750 0.2931 0.01307 0.00535 -0.0489 0.9017 1.0000
1.000 0.3261 0.01289 0.00515 -0.0496 0.8873 1.0000
1.250 0.3554 0.01275 0.00501 -0.0495 0.8718 1.0000
1.500 0.3843 0.01265 0.00492 -0.0494 0.8564 1.0000
1.750 0.4124 0.01257 0.00484 -0.0491 0.8406 1.0000
2.000 0.4402 0.01251 0.00479 -0.0487 0.8240 1.0000
2.250 0.4682 0.01246 0.00478 -0.0484 0.8067 1.0000
2.500 0.4937 0.01246 0.00481 -0.0476 0.7868 1.0000
2.750 0.5199 0.01246 0.00482 -0.0468 0.7650 1.0000
3.000 0.5444 0.01250 0.00488 -0.0458 0.7396 1.0000
3.250 0.5691 0.01255 0.00497 -0.0447 0.7099 1.0000
3.500 0.5929 0.01266 0.00506 -0.0435 0.6736 1.0000
3.750 0.6164 0.01281 0.00514 -0.0421 0.6272 1.0000
4.000 0.6387 0.01309 0.00524 -0.0406 0.5692 1.0000
4.250 0.6590 0.01354 0.00542 -0.0388 0.5023 1.0000
4.500 0.6780 0.01415 0.00577 -0.0370 0.4369 1.0000
4.750 0.6967 0.01482 0.00617 -0.0354 0.3789 1.0000
5.000 0.7162 0.01548 0.00662 -0.0340 0.3297 1.0000
5.250 0.7365 0.01610 0.00710 -0.0328 0.2897 1.0000
5.500 0.7572 0.01672 0.00762 -0.0317 0.2543 1.0000
5.750 0.7782 0.01733 0.00817 -0.0306 0.2193 1.0000
6.000 0.7988 0.01801 0.00877 -0.0296 0.1831 1.0000
6.250 0.8188 0.01881 0.00949 -0.0285 0.1361 1.0000
6.500 0.8375 0.01986 0.01030 -0.0273 0.0960 1.0000
6.750 0.8559 0.02101 0.01134 -0.0260 0.0735 1.0000
7.000 0.8742 0.02216 0.01251 -0.0246 0.0600 1.0000
7.250 0.8921 0.02335 0.01373 -0.0232 0.0501 1.0000
7.500 0.9100 0.02455 0.01505 -0.0218 0.0442 1.0000
7.750 0.9259 0.02611 0.01668 -0.0201 0.0407 1.0000
8.000 0.9445 0.02761 0.01841 -0.0187 0.0377 1.0000
8.250 0.9632 0.02914 0.02010 -0.0174 0.0345 1.0000
8.500 0.9790 0.03091 0.02197 -0.0162 0.0309 1.0000
8.750 0.9979 0.03292 0.02429 -0.0150 0.0289 1.0000
9.000 1.0155 0.03532 0.02706 -0.0136 0.0272 1.0000
9.250 1.0298 0.03745 0.02953 -0.0121 0.0248 1.0000
9.500 1.0415 0.03908 0.03133 -0.0106 0.0225 1.0000
9.750 1.0476 0.04230 0.03475 -0.0089 0.0209 1.0000
10.000 1.0514 0.04544 0.03831 -0.0065 0.0203 1.0000
10.250 1.0492 0.04878 0.04213 -0.0039 0.0198 1.0000
10.500 1.0409 0.05201 0.04573 -0.0009 0.0195 1.0000
10.750 1.0276 0.05536 0.04941 0.0019 0.0192 1.0000
11.000 1.0119 0.05901 0.05334 0.0037 0.0190 1.0000
11.250 0.9937 0.06316 0.05776 0.0043 0.0188 1.0000
11.500 0.9746 0.06799 0.06281 0.0033 0.0189 1.0000
11.750 0.9544 0.07371 0.06871 0.0007 0.0191 1.0000
12.000 0.9332 0.08065 0.07581 -0.0037 0.0193 1.0000
12.250 0.9141 0.08849 0.08375 -0.0092 0.0198 1.0000
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Polar data table (+)
Polar graphs
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