E220 (11.48%) (e220-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E220 (11.48%) (e220-il) Reynolds number: 500,000 Max Cl/Cd: 105.74 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e220-il-500000.txt Download as CSV file: xf-e220-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3972 0.08356 0.08110 -0.0168 0.7912 0.0204
-9.250 -0.4015 0.07832 0.07585 -0.0190 0.7868 0.0208
-9.000 -0.4083 0.07268 0.07020 -0.0217 0.7827 0.0211
-8.750 -0.4183 0.06646 0.06399 -0.0250 0.7784 0.0214
-8.500 -0.4345 0.05951 0.05704 -0.0296 0.7744 0.0213
-8.250 -0.4681 0.05147 0.04891 -0.0360 0.7705 0.0204
-8.000 -0.4923 0.04604 0.04339 -0.0359 0.7654 0.0203
-7.750 -0.5042 0.04078 0.03796 -0.0355 0.7607 0.0205
-6.500 -0.5174 0.02705 0.02164 -0.0264 0.7479 0.0182
-6.250 -0.5058 0.02054 0.01434 -0.0230 0.7443 0.0135
-6.000 -0.4826 0.01907 0.01258 -0.0220 0.7405 0.0133
-5.750 -0.4593 0.01740 0.01072 -0.0211 0.7362 0.0135
-5.500 -0.4355 0.01619 0.00940 -0.0204 0.7321 0.0140
-5.250 -0.4111 0.01535 0.00846 -0.0197 0.7285 0.0146
-5.000 -0.3863 0.01465 0.00767 -0.0191 0.7250 0.0155
-4.750 -0.3612 0.01398 0.00692 -0.0185 0.7211 0.0165
-4.500 -0.3359 0.01346 0.00630 -0.0179 0.7173 0.0174
-4.250 -0.3131 0.01260 0.00535 -0.0169 0.7140 0.0196
-4.000 -0.2873 0.01224 0.00496 -0.0165 0.7108 0.0225
-3.750 -0.2624 0.01164 0.00430 -0.0158 0.7073 0.0272
-3.500 -0.2370 0.01118 0.00383 -0.0152 0.7037 0.0377
-3.250 -0.2121 0.01069 0.00347 -0.0147 0.7005 0.0705
-3.000 -0.1874 0.01026 0.00324 -0.0142 0.6976 0.1256
-2.750 -0.1625 0.00981 0.00306 -0.0138 0.6943 0.1932
-2.500 -0.1381 0.00935 0.00290 -0.0133 0.6909 0.2744
-2.250 -0.1142 0.00890 0.00275 -0.0127 0.6876 0.3650
-2.000 -0.0915 0.00843 0.00263 -0.0118 0.6848 0.4705
-1.750 -0.0727 0.00782 0.00255 -0.0101 0.6819 0.6152
-1.500 -0.0549 0.00721 0.00251 -0.0078 0.6785 0.7600
-1.250 -0.0052 0.00696 0.00265 -0.0119 0.6753 0.8885
-1.000 0.0536 0.00721 0.00283 -0.0181 0.6723 0.9265
-0.750 0.0874 0.00747 0.00300 -0.0189 0.6694 0.9459
-0.500 0.1227 0.00767 0.00315 -0.0203 0.6661 0.9580
-0.250 0.1665 0.00781 0.00322 -0.0236 0.6624 0.9644
0.000 0.2047 0.00794 0.00329 -0.0257 0.6587 0.9722
0.250 0.2501 0.00805 0.00331 -0.0293 0.6552 0.9776
0.500 0.2885 0.00814 0.00337 -0.0316 0.6511 0.9839
0.750 0.3335 0.00809 0.00329 -0.0353 0.6466 0.9877
1.000 0.3748 0.00807 0.00321 -0.0383 0.6426 0.9926
1.250 0.4176 0.00799 0.00309 -0.0416 0.6384 0.9968
1.500 0.4565 0.00787 0.00297 -0.0441 0.6332 1.0000
1.750 0.4813 0.00785 0.00293 -0.0436 0.6286 1.0000
2.000 0.5062 0.00786 0.00290 -0.0431 0.6244 1.0000
2.250 0.5313 0.00784 0.00291 -0.0427 0.6191 1.0000
2.500 0.5565 0.00782 0.00288 -0.0423 0.6139 1.0000
2.750 0.5817 0.00784 0.00289 -0.0418 0.6087 1.0000
3.000 0.6071 0.00782 0.00290 -0.0414 0.6023 1.0000
3.250 0.6324 0.00783 0.00288 -0.0410 0.5969 1.0000
3.500 0.6579 0.00782 0.00294 -0.0406 0.5900 1.0000
3.750 0.6833 0.00783 0.00293 -0.0402 0.5830 1.0000
4.000 0.7089 0.00783 0.00298 -0.0398 0.5746 1.0000
4.250 0.7343 0.00785 0.00299 -0.0394 0.5663 1.0000
4.500 0.7597 0.00787 0.00305 -0.0389 0.5561 1.0000
4.750 0.7852 0.00790 0.00311 -0.0385 0.5445 1.0000
5.000 0.8104 0.00795 0.00318 -0.0381 0.5314 1.0000
5.250 0.8354 0.00803 0.00325 -0.0376 0.5144 1.0000
5.500 0.8600 0.00816 0.00336 -0.0371 0.4923 1.0000
5.750 0.8840 0.00836 0.00351 -0.0365 0.4655 1.0000
6.000 0.9072 0.00866 0.00371 -0.0359 0.4317 1.0000
6.250 0.9292 0.00909 0.00399 -0.0351 0.3926 1.0000
6.500 0.9491 0.00973 0.00441 -0.0341 0.3425 1.0000
6.750 0.9681 0.01041 0.00487 -0.0330 0.2948 1.0000
7.000 0.9867 0.01108 0.00535 -0.0318 0.2524 1.0000
7.250 1.0043 0.01179 0.00586 -0.0305 0.2125 1.0000
7.500 1.0222 0.01242 0.00636 -0.0291 0.1808 1.0000
7.750 1.0392 0.01307 0.00690 -0.0276 0.1525 1.0000
8.000 1.0551 0.01374 0.00746 -0.0260 0.1268 1.0000
8.250 1.0699 0.01444 0.00804 -0.0242 0.1042 1.0000
8.500 1.0841 0.01512 0.00864 -0.0222 0.0844 1.0000
8.750 1.0964 0.01585 0.00928 -0.0200 0.0674 1.0000
9.000 1.1070 0.01661 0.00998 -0.0175 0.0524 1.0000
9.250 1.1146 0.01747 0.01079 -0.0145 0.0390 1.0000
9.500 1.1197 0.01836 0.01166 -0.0112 0.0310 1.0000
9.750 1.1184 0.01916 0.01246 -0.0067 0.0270 1.0000
10.000 1.1152 0.02018 0.01353 -0.0024 0.0243 1.0000
10.250 1.1211 0.02104 0.01446 0.0002 0.0227 1.0000
10.500 1.1272 0.02204 0.01552 0.0024 0.0208 1.0000
10.750 1.1298 0.02339 0.01690 0.0047 0.0189 1.0000
11.000 1.1286 0.02516 0.01875 0.0071 0.0177 1.0000
11.250 1.1368 0.02634 0.02002 0.0086 0.0169 1.0000
11.500 1.1426 0.02776 0.02154 0.0101 0.0160 1.0000
11.750 1.1504 0.02906 0.02289 0.0113 0.0148 1.0000
12.000 1.1533 0.03082 0.02472 0.0127 0.0142 1.0000
12.250 1.1473 0.03337 0.02734 0.0144 0.0130 1.0000
12.500 1.1496 0.03530 0.02937 0.0156 0.0126 1.0000
12.750 1.1563 0.03688 0.03105 0.0165 0.0119 1.0000
13.000 1.1606 0.03872 0.03298 0.0173 0.0115 1.0000
13.250 1.1646 0.04062 0.03496 0.0181 0.0108 1.0000
13.500 1.1654 0.04285 0.03729 0.0190 0.0106 1.0000
13.750 1.1673 0.04505 0.03954 0.0195 0.0101 1.0000
14.000 1.1649 0.04770 0.04227 0.0201 0.0097 1.0000
14.250 1.1606 0.05067 0.04534 0.0209 0.0094 1.0000
14.500 1.1537 0.05403 0.04884 0.0217 0.0090 1.0000
14.750 1.1540 0.05674 0.05168 0.0219 0.0089 1.0000
15.000 1.1544 0.05959 0.05470 0.0216 0.0086 1.0000
15.250 1.1526 0.06274 0.05799 0.0214 0.0085 1.0000
15.500 1.1490 0.06624 0.06164 0.0209 0.0082 1.0000
15.750 1.1449 0.06990 0.06543 0.0203 0.0081 1.0000
16.000 1.1402 0.07380 0.06947 0.0193 0.0080 1.0000
16.250 1.1324 0.07830 0.07411 0.0181 0.0077 1.0000
16.500 1.1237 0.08301 0.07899 0.0167 0.0079 1.0000
16.750 1.1163 0.08780 0.08389 0.0148 0.0075 1.0000
17.000 1.1075 0.09290 0.08914 0.0127 0.0075 1.0000
17.250 1.0898 0.09976 0.09619 0.0100 0.0076 1.0000
17.500 1.0886 0.10392 0.10040 0.0077 0.0073 1.0000
17.750 1.0724 0.11099 0.10764 0.0043 0.0072 1.0000
18.000 1.0523 0.11906 0.11590 0.0004 0.0073 1.0000
18.250 1.0409 0.12573 0.12268 -0.0032 0.0072 1.0000
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