E220 (11.48%) (e220-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E220 (11.48%) (e220-il) Reynolds number: 50,000 Max Cl/Cd: 31.02 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e220-il-50000-n5.txt Download as CSV file: xf-e220-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E220 (11.48%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4449 0.09955 0.09318 -0.0251 1.0000 0.0434
-9.500 -0.4444 0.09505 0.08875 -0.0276 1.0000 0.0427
-9.250 -0.4452 0.09034 0.08413 -0.0305 1.0000 0.0420
-9.000 -0.4483 0.08514 0.07901 -0.0342 1.0000 0.0414
-8.750 -0.4538 0.07947 0.07343 -0.0390 1.0000 0.0406
-8.500 -0.4634 0.07411 0.06813 -0.0429 1.0000 0.0399
-8.250 -0.4758 0.06960 0.06365 -0.0446 1.0000 0.0393
-8.000 -0.4883 0.06527 0.05927 -0.0454 1.0000 0.0388
-7.750 -0.5026 0.06215 0.05610 -0.0441 1.0000 0.0384
-7.500 -0.5105 0.05848 0.05222 -0.0437 0.9869 0.0380
-7.250 -0.4991 0.05336 0.04666 -0.0464 0.9697 0.0380
-7.000 -0.4834 0.04935 0.04221 -0.0481 0.9561 0.0392
-6.750 -0.4662 0.04571 0.03807 -0.0491 0.9442 0.0409
-6.500 -0.4487 0.04239 0.03417 -0.0491 0.9329 0.0427
-6.250 -0.4289 0.03923 0.03037 -0.0488 0.9232 0.0443
-6.000 -0.4042 0.03630 0.02676 -0.0486 0.9154 0.0457
-5.750 -0.3809 0.03390 0.02403 -0.0482 0.9068 0.0476
-5.500 -0.3536 0.03225 0.02213 -0.0486 0.9001 0.0534
-5.250 -0.3277 0.03062 0.02007 -0.0480 0.8921 0.0590
-5.000 -0.2987 0.02901 0.01839 -0.0483 0.8864 0.0670
-4.750 -0.2740 0.02781 0.01707 -0.0477 0.8788 0.0790
-4.500 -0.2450 0.02656 0.01567 -0.0478 0.8731 0.0962
-4.000 -0.1960 0.02425 0.01369 -0.0473 0.8602 0.1870
-3.750 -0.1761 0.02315 0.01313 -0.0464 0.8540 0.2900
-3.500 -0.1610 0.02224 0.01285 -0.0443 0.8473 0.4235
-3.250 -0.1389 0.02133 0.01274 -0.0422 0.8429 0.6069
-3.000 -0.0457 0.02117 0.01278 -0.0509 0.8426 0.8385
-2.750 0.0098 0.02161 0.01282 -0.0549 0.8381 0.9055
-2.500 0.0659 0.02185 0.01263 -0.0600 0.8340 0.9520
-2.250 0.1296 0.02171 0.01209 -0.0672 0.8307 0.9861
-2.000 0.1727 0.02154 0.01160 -0.0711 0.8255 1.0000
-1.750 0.1915 0.02167 0.01155 -0.0704 0.8187 1.0000
-1.500 0.2113 0.02181 0.01149 -0.0695 0.8129 1.0000
-1.250 0.2300 0.02205 0.01159 -0.0687 0.8059 1.0000
-1.000 0.2508 0.02222 0.01157 -0.0678 0.8007 1.0000
-0.750 0.2698 0.02255 0.01179 -0.0671 0.7938 1.0000
-0.500 0.2907 0.02280 0.01191 -0.0662 0.7881 1.0000
-0.250 0.3104 0.02314 0.01215 -0.0653 0.7821 1.0000
0.000 0.3300 0.02349 0.01240 -0.0644 0.7757 1.0000
0.250 0.3519 0.02374 0.01255 -0.0634 0.7708 1.0000
0.500 0.3691 0.02425 0.01302 -0.0624 0.7634 1.0000
0.750 0.3908 0.02453 0.01323 -0.0614 0.7581 1.0000
1.000 0.4081 0.02507 0.01373 -0.0602 0.7508 1.0000
1.250 0.4291 0.02541 0.01403 -0.0591 0.7449 1.0000
1.500 0.4472 0.02590 0.01451 -0.0579 0.7379 1.0000
1.750 0.4672 0.02630 0.01489 -0.0567 0.7311 1.0000
2.000 0.4861 0.02676 0.01536 -0.0554 0.7242 1.0000
2.250 0.5054 0.02719 0.01579 -0.0541 0.7169 1.0000
2.500 0.5241 0.02765 0.01627 -0.0528 0.7095 1.0000
2.750 0.5438 0.02806 0.01670 -0.0515 0.7020 1.0000
3.000 0.5612 0.02859 0.01729 -0.0500 0.6937 1.0000
3.250 0.5831 0.02887 0.01762 -0.0488 0.6865 1.0000
3.500 0.5985 0.02948 0.01828 -0.0471 0.6769 1.0000
3.750 0.6240 0.02952 0.01841 -0.0461 0.6705 1.0000
4.000 0.6380 0.03018 0.01915 -0.0442 0.6596 1.0000
4.250 0.6563 0.03057 0.01963 -0.0426 0.6501 1.0000
4.500 0.6809 0.03057 0.01972 -0.0414 0.6422 1.0000
4.750 0.6958 0.03111 0.02037 -0.0394 0.6305 1.0000
5.000 0.7133 0.03147 0.02087 -0.0377 0.6195 1.0000
5.250 0.7378 0.03135 0.02088 -0.0363 0.6103 1.0000
5.500 0.7587 0.03138 0.02105 -0.0346 0.5991 1.0000
5.750 0.7756 0.03161 0.02142 -0.0326 0.5859 1.0000
6.000 0.7934 0.03172 0.02173 -0.0306 0.5725 1.0000
6.250 0.8122 0.03171 0.02188 -0.0286 0.5586 1.0000
6.500 0.8318 0.03157 0.02190 -0.0266 0.5441 1.0000
6.750 0.8528 0.03125 0.02176 -0.0245 0.5287 1.0000
7.000 0.8694 0.03117 0.02185 -0.0222 0.5107 1.0000
7.250 0.8840 0.03120 0.02208 -0.0196 0.4905 1.0000
7.500 0.9047 0.03074 0.02177 -0.0174 0.4693 1.0000
7.750 0.9212 0.03060 0.02174 -0.0148 0.4439 1.0000
8.000 0.9381 0.03047 0.02165 -0.0123 0.4149 1.0000
8.250 0.9514 0.03067 0.02181 -0.0095 0.3829 1.0000
8.500 0.9608 0.03120 0.02225 -0.0066 0.3495 1.0000
8.750 0.9657 0.03208 0.02298 -0.0034 0.3175 1.0000
9.000 0.9661 0.03327 0.02408 -0.0001 0.2887 1.0000
9.250 0.9653 0.03472 0.02541 0.0027 0.2612 1.0000
9.500 0.9649 0.03637 0.02695 0.0052 0.2355 1.0000
9.750 0.9645 0.03816 0.02863 0.0073 0.2118 1.0000
10.000 0.9645 0.04008 0.03047 0.0092 0.1901 1.0000
10.250 0.9648 0.04212 0.03243 0.0108 0.1699 1.0000
10.500 0.9649 0.04428 0.03452 0.0123 0.1510 1.0000
10.750 0.9656 0.04650 0.03667 0.0136 0.1350 1.0000
11.000 0.9656 0.04883 0.03893 0.0147 0.1203 1.0000
11.250 0.9669 0.05119 0.04128 0.0157 0.1072 1.0000
11.500 0.9692 0.05358 0.04372 0.0166 0.0957 1.0000
11.750 0.9728 0.05599 0.04626 0.0175 0.0858 1.0000
12.000 0.9761 0.05844 0.04875 0.0183 0.0780 1.0000
12.250 0.9799 0.06094 0.05135 0.0190 0.0710 1.0000
12.500 0.9889 0.06331 0.05386 0.0200 0.0657 1.0000
12.750 0.9926 0.06611 0.05688 0.0206 0.0607 1.0000
13.000 0.9976 0.06859 0.05928 0.0211 0.0566 1.0000
13.250 0.9958 0.07237 0.06347 0.0211 0.0536 1.0000
13.500 0.9940 0.07626 0.06766 0.0210 0.0516 1.0000
13.750 0.9894 0.08047 0.07212 0.0206 0.0502 1.0000
14.000 0.9814 0.08509 0.07696 0.0196 0.0490 1.0000
14.250 0.9710 0.09015 0.08222 0.0181 0.0482 1.0000
14.500 0.9602 0.09536 0.08756 0.0163 0.0472 1.0000
14.750 0.9486 0.10095 0.09329 0.0141 0.0464 1.0000
15.000 0.9037 0.11425 0.10697 0.0063 0.0489 1.0000
15.250 0.8633 0.12874 0.12158 -0.0023 0.0507 1.0000
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Polar data table (+)
Polar graphs
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