S2050 8.93% (s2050-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2050 8.93% (s2050-il) Reynolds number: 50,000 Max Cl/Cd: 33.24 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2050-il-50000.txt Download as CSV file: xf-s2050-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S2050 8.93%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5112 0.10907 0.10200 -0.0052 1.0000 0.2603
-8.750 -0.5038 0.10537 0.09833 -0.0045 1.0000 0.2746
-8.500 -0.5018 0.10220 0.09522 -0.0040 1.0000 0.2893
-8.250 -0.4984 0.09894 0.09202 -0.0033 1.0000 0.3039
-8.000 -0.4974 0.09583 0.08898 -0.0026 1.0000 0.3187
-7.750 -0.4933 0.09239 0.08556 -0.0017 1.0000 0.3332
-7.500 -0.4718 0.08767 0.08082 0.0000 1.0000 0.3529
-7.250 -0.5623 0.07063 0.06398 -0.0317 1.0000 0.1606
-7.000 -0.5690 0.06133 0.05429 -0.0376 1.0000 0.1290
-6.750 -0.5616 0.05646 0.04928 -0.0380 1.0000 0.1260
-6.500 -0.5544 0.05132 0.04382 -0.0390 1.0000 0.1241
-6.250 -0.5432 0.04647 0.03853 -0.0396 1.0000 0.1237
-6.000 -0.5279 0.04185 0.03338 -0.0399 1.0000 0.1242
-5.750 -0.5092 0.03782 0.02858 -0.0400 1.0000 0.1292
-5.500 -0.4888 0.03485 0.02545 -0.0393 1.0000 0.1401
-5.250 -0.4669 0.03209 0.02234 -0.0386 1.0000 0.1552
-5.000 -0.4431 0.02955 0.01927 -0.0380 1.0000 0.1734
-4.750 -0.4201 0.02734 0.01709 -0.0371 1.0000 0.1934
-4.500 -0.3965 0.02552 0.01517 -0.0362 1.0000 0.2202
-4.250 -0.3729 0.02385 0.01352 -0.0351 1.0000 0.2502
-4.000 -0.3494 0.02233 0.01207 -0.0339 1.0000 0.2881
-3.750 -0.3276 0.02086 0.01088 -0.0325 1.0000 0.3395
-3.500 -0.3065 0.01926 0.00985 -0.0309 1.0000 0.4238
-3.250 -0.2955 0.01804 0.00988 -0.0258 1.0000 0.5819
-3.000 -0.2951 0.01824 0.01051 -0.0168 1.0000 0.7275
-2.750 -0.2970 0.01839 0.01074 -0.0074 1.0000 0.8088
-2.500 -0.2904 0.01834 0.01062 0.0002 1.0000 0.8813
-2.250 -0.0736 0.01843 0.00925 -0.0308 1.0000 1.0000
-2.000 -0.0699 0.01801 0.00876 -0.0284 1.0000 1.0000
-1.750 -0.0675 0.01766 0.00835 -0.0255 1.0000 1.0000
-1.500 -0.0669 0.01735 0.00801 -0.0223 1.0000 1.0000
-1.250 -0.0681 0.01709 0.00771 -0.0187 1.0000 1.0000
-1.000 -0.0693 0.01687 0.00745 -0.0152 1.0000 1.0000
-0.750 -0.0632 0.01675 0.00725 -0.0129 1.0000 1.0000
-0.500 -0.0491 0.01676 0.00713 -0.0120 1.0000 1.0000
-0.250 -0.0310 0.01687 0.00711 -0.0117 1.0000 1.0000
0.000 -0.0111 0.01705 0.00718 -0.0117 1.0000 1.0000
0.250 0.0095 0.01731 0.00734 -0.0118 1.0000 1.0000
0.500 0.0301 0.01763 0.00758 -0.0120 1.0000 1.0000
0.750 0.0505 0.01803 0.00790 -0.0122 1.0000 1.0000
1.000 0.0705 0.01849 0.00831 -0.0125 1.0000 1.0000
1.250 0.0899 0.01902 0.00881 -0.0128 1.0000 1.0000
1.500 0.1088 0.01964 0.00941 -0.0131 1.0000 1.0000
1.750 0.1270 0.02034 0.01010 -0.0135 1.0000 1.0000
2.000 0.1567 0.02133 0.01112 -0.0162 0.9945 1.0000
2.250 0.2233 0.02264 0.01253 -0.0253 0.9685 1.0000
2.500 0.2871 0.02356 0.01360 -0.0330 0.9417 1.0000
2.750 0.3491 0.02412 0.01434 -0.0398 0.9138 1.0000
3.000 0.4104 0.02434 0.01481 -0.0456 0.8847 1.0000
3.250 0.4734 0.02415 0.01490 -0.0508 0.8549 1.0000
3.500 0.5315 0.02370 0.01475 -0.0543 0.8235 1.0000
3.750 0.5832 0.02311 0.01441 -0.0559 0.7901 1.0000
4.000 0.6283 0.02253 0.01400 -0.0559 0.7545 1.0000
4.250 0.6613 0.02231 0.01392 -0.0542 0.7144 1.0000
4.500 0.6898 0.02226 0.01391 -0.0520 0.6715 1.0000
4.750 0.7161 0.02232 0.01393 -0.0494 0.6263 1.0000
5.000 0.7398 0.02255 0.01412 -0.0468 0.5781 1.0000
5.250 0.7618 0.02296 0.01440 -0.0441 0.5265 1.0000
5.500 0.7827 0.02355 0.01480 -0.0415 0.4726 1.0000
5.750 0.8027 0.02432 0.01533 -0.0390 0.4170 1.0000
6.000 0.8218 0.02534 0.01608 -0.0367 0.3609 1.0000
6.250 0.8402 0.02663 0.01707 -0.0345 0.3062 1.0000
6.500 0.8587 0.02829 0.01855 -0.0325 0.2562 1.0000
6.750 0.8779 0.03017 0.02023 -0.0308 0.2135 1.0000
7.000 0.8978 0.03219 0.02207 -0.0293 0.1790 1.0000
7.250 0.9179 0.03456 0.02451 -0.0280 0.1534 1.0000
7.500 0.9400 0.03714 0.02709 -0.0270 0.1359 1.0000
7.750 0.9591 0.04016 0.03053 -0.0256 0.1248 1.0000
8.000 0.9772 0.04388 0.03460 -0.0244 0.1188 1.0000
8.250 0.9886 0.04755 0.03888 -0.0227 0.1137 1.0000
8.500 1.0081 0.05095 0.04217 -0.0222 0.1073 1.0000
8.750 1.0122 0.05539 0.04726 -0.0204 0.1064 1.0000
9.000 1.0147 0.06023 0.05257 -0.0190 0.1065 1.0000
9.250 1.0146 0.06537 0.05807 -0.0179 0.1070 1.0000
9.500 0.9841 0.07123 0.06462 -0.0168 0.1104 1.0000
9.750 0.9445 0.07784 0.07153 -0.0172 0.1142 1.0000
10.000 0.9172 0.08401 0.07777 -0.0188 0.1169 1.0000
10.250 0.9017 0.09047 0.08424 -0.0215 0.1192 1.0000
10.500 0.8415 0.10741 0.10104 -0.0371 0.1381 1.0000
10.750 0.8561 0.11087 0.10459 -0.0355 0.1352 1.0000
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Polar data table (+)
Polar graphs
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