S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il) Reynolds number: 50,000 Max Cl/Cd: 31.13 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7055-il-50000.txt Download as CSV file: xf-s7055-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S7055 (10.5%) Flat-Bottomed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3511 0.11441 0.10781 -0.0317 1.0000 0.1923
-9.000 -0.3264 0.10849 0.10187 -0.0299 1.0000 0.2026
-8.750 -0.3510 0.10891 0.10249 -0.0318 1.0000 0.2070
-8.500 -0.3270 0.10345 0.09701 -0.0298 1.0000 0.2188
-8.250 -0.3237 0.10025 0.09389 -0.0291 1.0000 0.2268
-8.000 -0.3395 0.09954 0.09335 -0.0288 1.0000 0.2351
-7.750 -0.3294 0.09588 0.08974 -0.0270 1.0000 0.2470
-7.500 -0.3304 0.09339 0.08736 -0.0250 1.0000 0.2590
-7.250 -0.3604 0.09356 0.08775 -0.0224 1.0000 0.2641
-7.000 -0.3624 0.09121 0.08550 -0.0192 1.0000 0.2778
-6.750 -0.3972 0.09151 0.08599 -0.0157 1.0000 0.2793
-6.500 -0.3769 0.08735 0.08184 -0.0121 1.0000 0.3009
-6.250 -0.4088 0.08734 0.08200 -0.0088 1.0000 0.3077
-6.000 -0.4164 0.08540 0.08015 -0.0055 1.0000 0.3220
-5.750 -0.4288 0.08376 0.07861 -0.0023 1.0000 0.3371
-5.500 -0.4426 0.08224 0.07719 0.0004 1.0000 0.3524
-5.250 -0.4315 0.07897 0.07397 0.0053 1.0000 0.3748
-5.000 -0.4499 0.07785 0.07294 0.0082 1.0000 0.3959
-4.750 -0.4447 0.07514 0.07027 0.0130 1.0000 0.4216
-4.500 -0.4487 0.07317 0.06837 0.0176 1.0000 0.4515
-3.750 -0.3786 0.05003 0.04329 -0.0301 1.0000 0.1770
-3.500 -0.3526 0.04504 0.03769 -0.0318 1.0000 0.1524
-3.250 -0.3289 0.04194 0.03397 -0.0322 1.0000 0.1467
-3.000 -0.3069 0.03924 0.03085 -0.0321 1.0000 0.1445
-2.750 -0.2834 0.03675 0.02782 -0.0319 1.0000 0.1421
-2.500 -0.2606 0.03505 0.02555 -0.0314 1.0000 0.1472
-2.250 -0.2393 0.03343 0.02368 -0.0308 1.0000 0.1531
-2.000 -0.2172 0.03221 0.02212 -0.0302 1.0000 0.1603
-1.750 -0.1961 0.03121 0.02096 -0.0296 1.0000 0.1730
-1.500 -0.1733 0.03028 0.01981 -0.0290 1.0000 0.1831
-1.250 -0.1505 0.02971 0.01916 -0.0286 0.9993 0.2033
-1.000 -0.1008 0.02922 0.01869 -0.0327 0.9897 0.2447
-0.750 -0.0369 0.02596 0.01801 -0.0376 0.9822 1.0000
-0.500 0.0070 0.02705 0.01841 -0.0415 0.9704 1.0000
-0.250 0.0451 0.02800 0.01891 -0.0446 0.9581 1.0000
0.000 0.0812 0.02893 0.01947 -0.0473 0.9456 1.0000
0.250 0.1166 0.02986 0.02011 -0.0498 0.9331 1.0000
0.500 0.1512 0.03080 0.02080 -0.0521 0.9205 1.0000
0.750 0.1854 0.03174 0.02151 -0.0542 0.9079 1.0000
1.000 0.2195 0.03268 0.02226 -0.0563 0.8953 1.0000
1.250 0.2543 0.03361 0.02303 -0.0584 0.8827 1.0000
1.500 0.2909 0.03454 0.02381 -0.0607 0.8704 1.0000
1.750 0.3172 0.03539 0.02456 -0.0613 0.8572 1.0000
2.000 0.3434 0.03626 0.02535 -0.0619 0.8440 1.0000
2.250 0.3698 0.03716 0.02617 -0.0624 0.8307 1.0000
2.500 0.3955 0.03807 0.02703 -0.0629 0.8176 1.0000
2.750 0.4218 0.03899 0.02790 -0.0633 0.8044 1.0000
3.000 0.4481 0.03991 0.02880 -0.0638 0.7913 1.0000
3.250 0.4747 0.04081 0.02970 -0.0641 0.7782 1.0000
3.500 0.5015 0.04172 0.03060 -0.0645 0.7650 1.0000
3.750 0.5288 0.04259 0.03148 -0.0649 0.7519 1.0000
4.000 0.5572 0.04343 0.03234 -0.0653 0.7390 1.0000
4.250 0.5873 0.04418 0.03316 -0.0657 0.7260 1.0000
4.500 0.6198 0.04480 0.03384 -0.0663 0.7131 1.0000
4.750 0.6407 0.04577 0.03486 -0.0657 0.6993 1.0000
5.000 0.6619 0.04674 0.03589 -0.0651 0.6855 1.0000
5.250 0.6832 0.04770 0.03696 -0.0645 0.6716 1.0000
5.500 0.7054 0.04862 0.03796 -0.0638 0.6576 1.0000
5.750 0.7273 0.04953 0.03897 -0.0631 0.6435 1.0000
6.000 0.7501 0.05037 0.03991 -0.0624 0.6293 1.0000
6.250 0.7733 0.05116 0.04085 -0.0616 0.6150 1.0000
6.500 0.7959 0.05196 0.04178 -0.0607 0.6008 1.0000
6.750 0.8204 0.05257 0.04252 -0.0598 0.5864 1.0000
7.000 0.8449 0.05312 0.04322 -0.0587 0.5719 1.0000
7.250 0.8726 0.05331 0.04362 -0.0576 0.5575 1.0000
7.500 0.9050 0.05295 0.04347 -0.0564 0.5430 1.0000
7.750 0.9544 0.05099 0.04179 -0.0556 0.5284 1.0000
8.000 1.0029 0.04900 0.04012 -0.0547 0.5125 1.0000
8.250 0.9780 0.05325 0.04437 -0.0513 0.4954 1.0000
8.500 1.0057 0.05286 0.04420 -0.0495 0.4781 1.0000
8.750 1.1256 0.04428 0.03614 -0.0506 0.4534 1.0000
9.000 1.1802 0.04151 0.03351 -0.0499 0.4264 1.0000
9.250 1.2142 0.04044 0.03248 -0.0483 0.3983 1.0000
9.500 1.2378 0.04013 0.03225 -0.0460 0.3694 1.0000
9.750 1.2546 0.04030 0.03243 -0.0432 0.3398 1.0000
10.000 1.2661 0.04072 0.03283 -0.0401 0.3093 1.0000
10.250 1.2746 0.04135 0.03337 -0.0367 0.2781 1.0000
10.500 1.2815 0.04218 0.03399 -0.0333 0.2466 1.0000
10.750 1.2867 0.04345 0.03492 -0.0301 0.2158 1.0000
11.000 1.2779 0.04555 0.03714 -0.0259 0.1945 1.0000
11.250 1.2764 0.04759 0.03899 -0.0225 0.1714 1.0000
11.500 1.2703 0.04998 0.04139 -0.0190 0.1539 1.0000
11.750 1.2759 0.05258 0.04370 -0.0169 0.1334 1.0000
12.000 1.2731 0.05543 0.04663 -0.0144 0.1202 1.0000
12.250 1.2623 0.05871 0.05026 -0.0118 0.1130 1.0000
12.500 1.2587 0.06219 0.05384 -0.0100 0.1045 1.0000
12.750 1.2658 0.06565 0.05722 -0.0089 0.0947 1.0000
13.000 1.2466 0.06979 0.06177 -0.0073 0.0933 1.0000
13.250 1.2264 0.07442 0.06675 -0.0066 0.0921 1.0000
13.500 1.2056 0.07954 0.07216 -0.0066 0.0916 1.0000
13.750 1.1830 0.08534 0.07822 -0.0076 0.0921 1.0000
14.000 1.1571 0.09183 0.08494 -0.0095 0.0928 1.0000
14.250 1.1317 0.09903 0.09231 -0.0123 0.0939 1.0000
14.500 1.1087 0.10665 0.10005 -0.0155 0.0949 1.0000
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Polar data table (+)
Polar graphs
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