E220 (11.48%) (e220-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E220 (11.48%) (e220-il) Reynolds number: 200,000 Max Cl/Cd: 72.47 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e220-il-200000-n5.txt Download as CSV file: xf-e220-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4690 0.08730 0.08400 -0.0248 0.8843 0.0128
-9.500 -0.4743 0.08220 0.07885 -0.0275 0.8615 0.0126
-9.250 -0.4822 0.07667 0.07329 -0.0308 0.8449 0.0124
-9.000 -0.4988 0.06919 0.06582 -0.0367 0.8304 0.0122
-8.750 -0.5197 0.06206 0.05856 -0.0410 0.8174 0.0120
-8.500 -0.5392 0.05657 0.05288 -0.0410 0.8071 0.0117
-8.250 -0.5544 0.05071 0.04673 -0.0404 0.7991 0.0115
-8.000 -0.5664 0.04461 0.04022 -0.0388 0.7915 0.0113
-7.500 -0.5689 0.03480 0.02934 -0.0343 0.7794 0.0110
-7.250 -0.5598 0.03133 0.02533 -0.0321 0.7739 0.0111
-7.000 -0.5457 0.02854 0.02204 -0.0303 0.7688 0.0112
-6.750 -0.5279 0.02626 0.01932 -0.0289 0.7632 0.0115
-6.500 -0.5080 0.02437 0.01704 -0.0276 0.7586 0.0118
-6.250 -0.4861 0.02271 0.01505 -0.0265 0.7542 0.0123
-6.000 -0.4630 0.02130 0.01337 -0.0256 0.7493 0.0130
-5.750 -0.4391 0.02027 0.01210 -0.0248 0.7451 0.0137
-5.500 -0.4163 0.01928 0.01102 -0.0241 0.7411 0.0152
-5.250 -0.3920 0.01850 0.01016 -0.0236 0.7364 0.0164
-5.000 -0.3681 0.01764 0.00915 -0.0228 0.7324 0.0177
-4.750 -0.3442 0.01692 0.00825 -0.0219 0.7289 0.0192
-4.500 -0.3208 0.01613 0.00741 -0.0211 0.7250 0.0214
-4.250 -0.2957 0.01565 0.00685 -0.0206 0.7207 0.0261
-4.000 -0.2713 0.01508 0.00624 -0.0200 0.7171 0.0335
-3.750 -0.2465 0.01460 0.00571 -0.0194 0.7141 0.0458
-3.500 -0.2218 0.01408 0.00531 -0.0189 0.7103 0.0723
-3.250 -0.1971 0.01362 0.00498 -0.0185 0.7063 0.1088
-3.000 -0.1726 0.01317 0.00470 -0.0180 0.7028 0.1599
-2.750 -0.1486 0.01272 0.00444 -0.0174 0.6999 0.2248
-2.500 -0.1259 0.01218 0.00426 -0.0167 0.6965 0.3182
-2.250 -0.1037 0.01168 0.00411 -0.0158 0.6926 0.4136
-2.000 -0.0823 0.01121 0.00397 -0.0146 0.6892 0.5105
-1.750 -0.0620 0.01070 0.00385 -0.0129 0.6862 0.6220
-1.500 -0.0346 0.01020 0.00385 -0.0122 0.6834 0.7613
-1.250 0.0470 0.01023 0.00407 -0.0227 0.6799 0.8779
-1.000 0.0937 0.01041 0.00415 -0.0263 0.6764 0.9089
-0.750 0.1267 0.01058 0.00422 -0.0271 0.6732 0.9315
-0.500 0.1616 0.01074 0.00425 -0.0283 0.6703 0.9483
-0.250 0.1978 0.01088 0.00433 -0.0300 0.6666 0.9611
0.000 0.2344 0.01099 0.00438 -0.0319 0.6626 0.9717
0.250 0.2759 0.01103 0.00434 -0.0348 0.6590 0.9800
0.500 0.3169 0.01105 0.00426 -0.0376 0.6559 0.9873
0.750 0.3580 0.01105 0.00425 -0.0407 0.6514 0.9943
1.000 0.4001 0.01096 0.00412 -0.0439 0.6465 1.0000
1.250 0.4246 0.01096 0.00407 -0.0433 0.6424 1.0000
1.500 0.4494 0.01098 0.00408 -0.0429 0.6375 1.0000
1.750 0.4743 0.01100 0.00411 -0.0425 0.6323 1.0000
2.000 0.4990 0.01101 0.00408 -0.0419 0.6279 1.0000
2.250 0.5240 0.01104 0.00413 -0.0415 0.6221 1.0000
2.500 0.5490 0.01106 0.00417 -0.0410 0.6161 1.0000
2.750 0.5739 0.01109 0.00418 -0.0405 0.6108 1.0000
3.000 0.5989 0.01113 0.00427 -0.0401 0.6038 1.0000
3.250 0.6238 0.01115 0.00427 -0.0395 0.5981 1.0000
3.500 0.6488 0.01120 0.00441 -0.0391 0.5898 1.0000
3.750 0.6736 0.01123 0.00444 -0.0385 0.5826 1.0000
4.000 0.6985 0.01128 0.00455 -0.0380 0.5734 1.0000
4.250 0.7232 0.01133 0.00465 -0.0375 0.5639 1.0000
4.500 0.7478 0.01138 0.00474 -0.0369 0.5536 1.0000
4.750 0.7723 0.01144 0.00483 -0.0362 0.5415 1.0000
5.000 0.7965 0.01152 0.00494 -0.0356 0.5269 1.0000
5.250 0.8205 0.01162 0.00508 -0.0349 0.5093 1.0000
5.500 0.8440 0.01176 0.00524 -0.0341 0.4883 1.0000
5.750 0.8667 0.01196 0.00540 -0.0333 0.4622 1.0000
6.000 0.8882 0.01226 0.00561 -0.0322 0.4299 1.0000
6.250 0.9079 0.01272 0.00592 -0.0310 0.3904 1.0000
6.500 0.9260 0.01332 0.00634 -0.0296 0.3495 1.0000
6.750 0.9432 0.01398 0.00688 -0.0281 0.3122 1.0000
7.000 0.9600 0.01464 0.00743 -0.0266 0.2786 1.0000
7.250 0.9760 0.01533 0.00802 -0.0250 0.2482 1.0000
7.500 0.9903 0.01610 0.00866 -0.0232 0.2169 1.0000
7.750 1.0028 0.01694 0.00936 -0.0211 0.1838 1.0000
8.000 1.0136 0.01782 0.01009 -0.0188 0.1527 1.0000
8.250 1.0234 0.01871 0.01087 -0.0164 0.1261 1.0000
8.500 1.0331 0.01954 0.01163 -0.0140 0.1077 1.0000
8.750 1.0419 0.02037 0.01241 -0.0114 0.0919 1.0000
9.000 1.0491 0.02122 0.01324 -0.0087 0.0782 1.0000
9.250 1.0514 0.02208 0.01407 -0.0051 0.0673 1.0000
9.500 1.0540 0.02300 0.01499 -0.0019 0.0584 1.0000
9.750 1.0587 0.02400 0.01602 0.0007 0.0508 1.0000
10.000 1.0627 0.02519 0.01722 0.0030 0.0440 1.0000
10.250 1.0677 0.02643 0.01853 0.0051 0.0381 1.0000
10.500 1.0721 0.02783 0.01996 0.0070 0.0338 1.0000
10.750 1.0779 0.02920 0.02141 0.0086 0.0300 1.0000
11.000 1.0801 0.03091 0.02313 0.0103 0.0267 1.0000
11.250 1.0855 0.03244 0.02476 0.0117 0.0250 1.0000
11.500 1.0911 0.03400 0.02644 0.0129 0.0233 1.0000
11.750 1.0956 0.03570 0.02823 0.0141 0.0217 1.0000
12.000 1.0978 0.03764 0.03022 0.0151 0.0201 1.0000
12.250 1.0977 0.03987 0.03253 0.0162 0.0191 1.0000
12.500 1.1025 0.04169 0.03449 0.0171 0.0181 1.0000
12.750 1.1059 0.04369 0.03664 0.0179 0.0170 1.0000
13.000 1.1092 0.04575 0.03879 0.0184 0.0157 1.0000
13.250 1.1102 0.04808 0.04121 0.0189 0.0149 1.0000
13.500 1.1081 0.05079 0.04400 0.0194 0.0142 1.0000
13.750 1.1060 0.05359 0.04690 0.0197 0.0136 1.0000
14.000 1.1065 0.05625 0.04972 0.0200 0.0131 1.0000
14.250 1.1063 0.05908 0.05271 0.0200 0.0125 1.0000
14.500 1.1053 0.06210 0.05587 0.0199 0.0118 1.0000
14.750 1.1033 0.06532 0.05923 0.0196 0.0115 1.0000
15.000 1.1013 0.06868 0.06271 0.0189 0.0110 1.0000
15.250 1.0977 0.07234 0.06649 0.0182 0.0107 1.0000
15.500 1.0926 0.07638 0.07061 0.0168 0.0101 1.0000
15.750 1.0866 0.08059 0.07495 0.0156 0.0099 1.0000
16.000 1.0784 0.08534 0.07982 0.0141 0.0095 1.0000
16.250 1.0721 0.09005 0.08473 0.0123 0.0093 1.0000
16.500 1.0630 0.09542 0.09031 0.0101 0.0089 1.0000
16.750 1.0540 0.10088 0.09594 0.0078 0.0088 1.0000
17.000 1.0429 0.10698 0.10222 0.0049 0.0086 1.0000
17.250 1.0308 0.11343 0.10884 0.0018 0.0085 1.0000
17.500 1.0191 0.11997 0.11554 -0.0015 0.0086 1.0000
17.750 1.0043 0.12752 0.12325 -0.0054 0.0085 1.0000
18.000 0.9897 0.13532 0.13120 -0.0097 0.0085 1.0000
18.250 0.9724 0.14411 0.14015 -0.0145 0.0085 1.0000
18.500 0.9550 0.15335 0.14953 -0.0196 0.0086 1.0000
18.750 0.9341 0.16406 0.16035 -0.0254 0.0090 1.0000
19.000 0.9056 0.17815 0.17453 -0.0328 0.0093 1.0000
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Polar data table (+)
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