E203 (13.64%) (e203-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E203 (13.64%) (e203-il) Reynolds number: 50,000 Max Cl/Cd: 32.01 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e203-il-50000.txt Download as CSV file: xf-e203-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E203 (13.64%)
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 -0.3669 0.10620 0.09933 -0.0285 1.0000 0.3014
-9.000 -0.4708 0.08220 0.07574 -0.0517 1.0000 0.1393
-8.750 -0.4866 0.07694 0.07057 -0.0529 1.0000 0.1340
-8.500 -0.5688 0.06863 0.06227 -0.0565 1.0000 0.1225
-8.250 -0.5768 0.06488 0.05852 -0.0551 1.0000 0.1210
-8.000 -0.5905 0.06111 0.05469 -0.0535 1.0000 0.1193
-7.750 -0.6048 0.05730 0.05071 -0.0519 1.0000 0.1180
-7.500 -0.6153 0.05358 0.04673 -0.0502 1.0000 0.1168
-7.250 -0.6199 0.05016 0.04299 -0.0485 1.0000 0.1170
-7.000 -0.6194 0.04701 0.03947 -0.0470 1.0000 0.1180
-6.750 -0.6146 0.04400 0.03603 -0.0455 1.0000 0.1196
-6.500 -0.6058 0.04114 0.03265 -0.0443 1.0000 0.1214
-6.250 -0.5930 0.03854 0.02947 -0.0430 1.0000 0.1234
-6.000 -0.5773 0.03633 0.02730 -0.0418 1.0000 0.1282
-5.750 -0.5606 0.03459 0.02517 -0.0407 1.0000 0.1365
-5.500 -0.5436 0.03295 0.02353 -0.0396 1.0000 0.1479
-5.250 -0.5255 0.03129 0.02177 -0.0383 1.0000 0.1641
-5.000 -0.5087 0.02977 0.02043 -0.0371 1.0000 0.1917
-4.750 -0.4924 0.02830 0.01921 -0.0359 1.0000 0.2396
-4.500 -0.4783 0.02726 0.01882 -0.0343 1.0000 0.3093
-4.250 -0.4652 0.02728 0.01935 -0.0316 1.0000 0.3873
-4.000 -0.4531 0.02784 0.02014 -0.0283 1.0000 0.4537
-3.750 -0.4422 0.02844 0.02088 -0.0246 1.0000 0.5049
-3.500 -0.4313 0.02889 0.02138 -0.0209 1.0000 0.5490
-3.250 -0.4200 0.02918 0.02164 -0.0176 1.0000 0.5893
-3.000 -0.4094 0.02940 0.02186 -0.0141 1.0000 0.6230
-2.750 -0.3987 0.02952 0.02193 -0.0108 1.0000 0.6544
-2.250 -0.3502 0.03039 0.02262 -0.0086 0.9855 0.7219
-2.000 -0.3266 0.03065 0.02275 -0.0078 0.9772 0.7522
-1.750 -0.3007 0.03097 0.02294 -0.0074 0.9695 0.7816
-1.500 -0.2792 0.03105 0.02291 -0.0066 0.9613 0.8090
-1.250 -0.2551 0.03122 0.02297 -0.0063 0.9537 0.8372
-1.000 -0.2308 0.03135 0.02300 -0.0061 0.9461 0.8656
-0.750 -0.2006 0.03158 0.02315 -0.0072 0.9384 0.8963
-0.500 -0.1445 0.03224 0.02366 -0.0134 0.9305 0.9301
-0.250 -0.0652 0.03316 0.02438 -0.0249 0.9218 0.9619
0.000 0.0409 0.03431 0.02526 -0.0418 0.9133 0.9921
0.250 0.0325 0.03387 0.02477 -0.0400 0.9051 1.0000
0.500 0.0487 0.03399 0.02470 -0.0419 0.8976 1.0000
0.750 0.0685 0.03444 0.02495 -0.0437 0.8900 1.0000
1.000 0.1058 0.03533 0.02561 -0.0477 0.8826 1.0000
1.250 0.1263 0.03608 0.02620 -0.0487 0.8750 1.0000
1.500 0.1627 0.03714 0.02708 -0.0518 0.8680 1.0000
1.750 0.1779 0.03799 0.02781 -0.0516 0.8608 1.0000
2.000 0.2160 0.03916 0.02885 -0.0547 0.8536 1.0000
2.250 0.2258 0.04008 0.02970 -0.0536 0.8466 1.0000
2.500 0.2641 0.04129 0.03083 -0.0565 0.8389 1.0000
2.750 0.2713 0.04233 0.03182 -0.0551 0.8322 1.0000
3.000 0.3075 0.04357 0.03301 -0.0575 0.8241 1.0000
3.250 0.3147 0.04473 0.03414 -0.0562 0.8173 1.0000
3.500 0.3527 0.04603 0.03543 -0.0588 0.8085 1.0000
3.750 0.3563 0.04728 0.03666 -0.0571 0.8016 1.0000
4.000 0.3899 0.04861 0.03800 -0.0589 0.7920 1.0000
4.250 0.3983 0.04994 0.03936 -0.0579 0.7840 1.0000
4.500 0.4228 0.05133 0.04077 -0.0587 0.7742 1.0000
4.750 0.4602 0.05265 0.04214 -0.0607 0.7628 1.0000
5.000 0.4608 0.05416 0.04367 -0.0589 0.7536 1.0000
5.250 0.4827 0.05558 0.04517 -0.0592 0.7418 1.0000
5.500 0.5092 0.05696 0.04662 -0.0599 0.7290 1.0000
5.750 0.5369 0.05828 0.04803 -0.0605 0.7153 1.0000
6.000 0.5650 0.05956 0.04942 -0.0611 0.7012 1.0000
6.250 0.5913 0.06082 0.05078 -0.0614 0.6865 1.0000
6.500 0.6122 0.06211 0.05219 -0.0611 0.6710 1.0000
6.750 0.6307 0.06348 0.05366 -0.0606 0.6551 1.0000
7.000 0.6467 0.06490 0.05521 -0.0599 0.6383 1.0000
7.250 0.6638 0.06627 0.05670 -0.0591 0.6206 1.0000
7.500 0.6871 0.06733 0.05791 -0.0586 0.6021 1.0000
7.750 0.7233 0.06761 0.05840 -0.0584 0.5833 1.0000
8.000 0.7531 0.06799 0.05899 -0.0576 0.5639 1.0000
8.250 0.7636 0.06942 0.06055 -0.0562 0.5435 1.0000
8.500 0.8135 0.06774 0.05917 -0.0550 0.5228 1.0000
8.750 0.8298 0.06843 0.06005 -0.0532 0.5011 1.0000
9.000 0.9047 0.06258 0.05468 -0.0504 0.4782 1.0000
9.250 1.1386 0.03739 0.03040 -0.0479 0.4155 1.0000
9.500 1.1514 0.03615 0.02897 -0.0431 0.3655 1.0000
9.750 1.1583 0.03619 0.02844 -0.0385 0.3140 1.0000
10.000 1.1551 0.03780 0.02967 -0.0341 0.2732 1.0000
10.250 1.1559 0.03997 0.03148 -0.0307 0.2361 1.0000
10.500 1.1601 0.04234 0.03356 -0.0279 0.2038 1.0000
10.750 1.1669 0.04488 0.03588 -0.0257 0.1760 1.0000
11.000 1.1773 0.04757 0.03841 -0.0239 0.1517 1.0000
11.250 1.1848 0.05031 0.04113 -0.0221 0.1331 1.0000
11.500 1.2006 0.05333 0.04410 -0.0210 0.1172 1.0000
11.750 1.2079 0.05679 0.04781 -0.0194 0.1080 1.0000
12.000 1.2232 0.06038 0.05144 -0.0187 0.0995 1.0000
12.250 1.2136 0.06391 0.05539 -0.0163 0.0969 1.0000
12.500 1.2051 0.06776 0.05958 -0.0145 0.0948 1.0000
12.750 1.1958 0.07176 0.06386 -0.0132 0.0931 1.0000
13.000 1.2149 0.07619 0.06819 -0.0132 0.0881 1.0000
13.250 1.1944 0.08051 0.07281 -0.0121 0.0880 1.0000
13.500 1.1731 0.08531 0.07788 -0.0118 0.0880 1.0000
13.750 1.1502 0.09066 0.08345 -0.0123 0.0882 1.0000
14.000 1.0540 0.10270 0.09612 -0.0193 0.0978 1.0000
14.250 1.0251 0.11120 0.10472 -0.0234 0.0994 1.0000
14.500 1.0026 0.11981 0.11339 -0.0277 0.1006 1.0000
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Polar data table (+)
Polar graphs
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