E205 (10.48%) (e205-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E205 (10.48%) (e205-il) Reynolds number: 500,000 Max Cl/Cd: 98.86 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e205-il-500000-n5.txt Download as CSV file: xf-e205-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E205 (10.48%)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5567 0.04953 0.04735 -0.0505 1.0000 0.0095
-8.750 -0.5863 0.04025 0.03764 -0.0521 1.0000 0.0094
-8.500 -0.5863 0.03278 0.02957 -0.0552 0.9877 0.0095
-8.250 -0.5698 0.02840 0.02474 -0.0569 0.9757 0.0097
-8.000 -0.5472 0.02570 0.02171 -0.0581 0.9611 0.0099
-7.750 -0.5204 0.02346 0.01916 -0.0594 0.9417 0.0101
-7.500 -0.4926 0.02182 0.01724 -0.0603 0.9139 0.0104
-7.250 -0.4698 0.02054 0.01566 -0.0598 0.8814 0.0106
-7.000 -0.4491 0.01941 0.01419 -0.0587 0.8504 0.0109
-6.750 -0.4280 0.01834 0.01282 -0.0575 0.8235 0.0110
-6.500 -0.4060 0.01739 0.01160 -0.0565 0.7997 0.0113
-6.250 -0.3831 0.01653 0.01050 -0.0557 0.7785 0.0115
-6.000 -0.3594 0.01582 0.00958 -0.0549 0.7591 0.0118
-5.750 -0.3351 0.01522 0.00879 -0.0543 0.7417 0.0123
-5.500 -0.3107 0.01457 0.00794 -0.0536 0.7259 0.0126
-5.250 -0.2861 0.01393 0.00714 -0.0530 0.7112 0.0128
-4.750 -0.2361 0.01285 0.00578 -0.0518 0.6854 0.0132
-4.500 -0.2106 0.01243 0.00525 -0.0513 0.6737 0.0135
-4.250 -0.1848 0.01207 0.00477 -0.0508 0.6630 0.0137
-4.000 -0.1599 0.01151 0.00409 -0.0502 0.6531 0.0143
-3.750 -0.1341 0.01113 0.00362 -0.0498 0.6432 0.0150
-3.500 -0.1077 0.01086 0.00327 -0.0495 0.6344 0.0157
-3.250 -0.0812 0.01065 0.00297 -0.0491 0.6259 0.0164
-3.000 -0.0543 0.01046 0.00271 -0.0489 0.6175 0.0174
-2.750 -0.0275 0.01031 0.00247 -0.0486 0.6099 0.0189
-2.500 -0.0004 0.01014 0.00226 -0.0484 0.6024 0.0209
-2.250 0.0262 0.00994 0.00207 -0.0481 0.5954 0.0320
-2.000 0.0527 0.00969 0.00191 -0.0478 0.5883 0.0636
-1.750 0.0790 0.00947 0.00179 -0.0476 0.5819 0.1017
-1.500 0.1058 0.00926 0.00170 -0.0474 0.5754 0.1419
-1.250 0.1321 0.00906 0.00162 -0.0472 0.5690 0.1897
-1.000 0.1579 0.00873 0.00156 -0.0469 0.5632 0.2761
-0.750 0.1826 0.00832 0.00152 -0.0465 0.5572 0.3942
-0.500 0.2076 0.00802 0.00150 -0.0460 0.5516 0.4913
-0.250 0.2314 0.00764 0.00149 -0.0453 0.5458 0.6081
0.000 0.2542 0.00731 0.00150 -0.0441 0.5404 0.7171
0.250 0.2766 0.00698 0.00154 -0.0426 0.5352 0.8300
0.500 0.3252 0.00693 0.00166 -0.0466 0.5286 0.9366
0.750 0.3638 0.00702 0.00169 -0.0488 0.5231 0.9626
1.000 0.3992 0.00710 0.00173 -0.0504 0.5169 0.9757
1.250 0.4359 0.00719 0.00175 -0.0523 0.5112 0.9850
1.500 0.4758 0.00724 0.00177 -0.0549 0.5053 0.9915
1.750 0.5151 0.00730 0.00178 -0.0575 0.4990 0.9968
2.000 0.5512 0.00736 0.00181 -0.0593 0.4933 1.0000
2.250 0.5763 0.00742 0.00185 -0.0588 0.4872 1.0000
2.500 0.6012 0.00752 0.00191 -0.0582 0.4815 1.0000
2.750 0.6264 0.00758 0.00197 -0.0576 0.4747 1.0000
3.000 0.6512 0.00769 0.00204 -0.0570 0.4677 1.0000
3.250 0.6763 0.00777 0.00212 -0.0564 0.4594 1.0000
3.500 0.7011 0.00788 0.00221 -0.0558 0.4514 1.0000
3.750 0.7260 0.00799 0.00231 -0.0552 0.4424 1.0000
4.000 0.7508 0.00810 0.00241 -0.0546 0.4333 1.0000
4.250 0.7754 0.00824 0.00252 -0.0540 0.4237 1.0000
4.500 0.8000 0.00837 0.00266 -0.0534 0.4131 1.0000
4.750 0.8246 0.00851 0.00280 -0.0527 0.4022 1.0000
5.000 0.8489 0.00868 0.00295 -0.0521 0.3899 1.0000
5.250 0.8728 0.00887 0.00311 -0.0514 0.3753 1.0000
5.500 0.8967 0.00907 0.00329 -0.0506 0.3605 1.0000
5.750 0.9200 0.00932 0.00351 -0.0498 0.3425 1.0000
6.000 0.9425 0.00962 0.00374 -0.0489 0.3181 1.0000
6.250 0.9619 0.01018 0.00408 -0.0476 0.2727 1.0000
6.500 0.9787 0.01098 0.00457 -0.0460 0.2157 1.0000
6.750 0.9954 0.01178 0.00511 -0.0443 0.1660 1.0000
7.000 1.0138 0.01244 0.00562 -0.0429 0.1327 1.0000
7.250 1.0331 0.01302 0.00608 -0.0417 0.1085 1.0000
7.500 1.0525 0.01358 0.00656 -0.0404 0.0876 1.0000
7.750 1.0710 0.01420 0.00708 -0.0391 0.0679 1.0000
8.000 1.0894 0.01481 0.00761 -0.0377 0.0510 1.0000
8.250 1.1062 0.01552 0.00824 -0.0362 0.0343 1.0000
8.500 1.1215 0.01632 0.00895 -0.0344 0.0185 1.0000
8.750 1.1365 0.01710 0.00968 -0.0326 0.0098 1.0000
9.000 1.1532 0.01773 0.01034 -0.0310 0.0081 1.0000
9.250 1.1686 0.01841 0.01107 -0.0293 0.0070 1.0000
9.500 1.1847 0.01899 0.01173 -0.0276 0.0067 1.0000
9.750 1.1985 0.01963 0.01246 -0.0256 0.0063 1.0000
10.000 1.2092 0.02030 0.01322 -0.0232 0.0061 1.0000
10.250 1.2180 0.02109 0.01410 -0.0205 0.0058 1.0000
10.500 1.2270 0.02192 0.01501 -0.0182 0.0057 1.0000
10.750 1.2341 0.02292 0.01610 -0.0158 0.0054 1.0000
11.000 1.2410 0.02402 0.01728 -0.0137 0.0052 1.0000
11.250 1.2464 0.02530 0.01866 -0.0118 0.0051 1.0000
11.500 1.2484 0.02696 0.02041 -0.0100 0.0047 1.0000
11.750 1.2517 0.02867 0.02221 -0.0086 0.0047 1.0000
12.000 1.2491 0.03103 0.02470 -0.0073 0.0044 1.0000
12.250 1.2474 0.03350 0.02727 -0.0064 0.0043 1.0000
12.500 1.2520 0.03547 0.02935 -0.0059 0.0043 1.0000
12.750 1.2538 0.03781 0.03181 -0.0055 0.0042 1.0000
13.000 1.2558 0.04022 0.03431 -0.0052 0.0042 1.0000
13.250 1.2556 0.04291 0.03712 -0.0051 0.0041 1.0000
13.500 1.2548 0.04575 0.04006 -0.0051 0.0041 1.0000
13.750 1.2540 0.04864 0.04306 -0.0052 0.0040 1.0000
14.000 1.2526 0.05166 0.04619 -0.0055 0.0040 1.0000
14.250 1.2501 0.05491 0.04955 -0.0059 0.0040 1.0000
14.500 1.2464 0.05838 0.05313 -0.0065 0.0039 1.0000
14.750 1.2434 0.06190 0.05677 -0.0072 0.0039 1.0000
15.000 1.2398 0.06562 0.06060 -0.0081 0.0039 1.0000
15.250 1.2363 0.06943 0.06452 -0.0091 0.0038 1.0000
15.500 1.2321 0.07348 0.06870 -0.0104 0.0037 1.0000
15.750 1.2261 0.07791 0.07324 -0.0118 0.0037 1.0000
16.000 1.2212 0.08230 0.07775 -0.0133 0.0037 1.0000
16.250 1.2160 0.08685 0.08243 -0.0151 0.0036 1.0000
16.500 1.2084 0.09194 0.08765 -0.0171 0.0036 1.0000
16.750 1.2020 0.09696 0.09279 -0.0192 0.0036 1.0000
17.000 1.1941 0.10239 0.09837 -0.0217 0.0035 1.0000
17.250 1.1863 0.10790 0.10400 -0.0242 0.0036 1.0000
17.500 1.1784 0.11364 0.10987 -0.0270 0.0035 1.0000
17.750 1.1698 0.11958 0.11593 -0.0300 0.0035 1.0000
18.000 1.1603 0.12593 0.12241 -0.0333 0.0035 1.0000
18.250 1.1511 0.13230 0.12891 -0.0368 0.0034 1.0000
18.500 1.1414 0.13896 0.13570 -0.0404 0.0035 1.0000
18.750 1.1313 0.14585 0.14272 -0.0443 0.0035 1.0000
19.000 1.1206 0.15311 0.15010 -0.0485 0.0035 1.0000
19.250 1.1108 0.16034 0.15746 -0.0528 0.0035 1.0000
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