E220 (11.48%) (e220-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E220 (11.48%) (e220-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.38 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e220-il-1000000-n5.txt Download as CSV file: xf-e220-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.8086 0.04525 0.04283 -0.0436 0.7626 0.0029
-11.250 -0.8467 0.03998 0.03727 -0.0411 0.7536 0.0029
-11.000 -0.8839 0.03483 0.03172 -0.0359 0.7454 0.0028
-10.750 -0.8852 0.03210 0.02872 -0.0335 0.7388 0.0029
-10.500 -0.8758 0.03036 0.02679 -0.0319 0.7320 0.0030
-10.250 -0.8710 0.02783 0.02394 -0.0296 0.7264 0.0031
-10.000 -0.8605 0.02581 0.02166 -0.0278 0.7210 0.0031
-9.750 -0.8474 0.02403 0.01960 -0.0262 0.7159 0.0032
-9.500 -0.8308 0.02262 0.01798 -0.0248 0.7114 0.0033
-9.250 -0.8128 0.02134 0.01650 -0.0236 0.7066 0.0033
-9.000 -0.7922 0.02042 0.01542 -0.0227 0.7018 0.0035
-8.750 -0.7722 0.01934 0.01414 -0.0216 0.6976 0.0035
-8.500 -0.7515 0.01830 0.01293 -0.0206 0.6935 0.0036
-8.250 -0.7294 0.01747 0.01195 -0.0198 0.6896 0.0036
-8.000 -0.7065 0.01675 0.01109 -0.0191 0.6858 0.0037
-7.750 -0.6831 0.01606 0.01027 -0.0184 0.6823 0.0037
-7.500 -0.6593 0.01544 0.00954 -0.0178 0.6785 0.0038
-7.250 -0.6351 0.01485 0.00885 -0.0172 0.6748 0.0038
-7.000 -0.6126 0.01399 0.00783 -0.0163 0.6715 0.0040
-6.750 -0.5891 0.01328 0.00701 -0.0156 0.6686 0.0042
-6.500 -0.5641 0.01280 0.00647 -0.0151 0.6654 0.0044
-6.250 -0.5383 0.01244 0.00605 -0.0148 0.6619 0.0047
-6.000 -0.5127 0.01206 0.00560 -0.0144 0.6587 0.0050
-5.500 -0.4608 0.01136 0.00478 -0.0137 0.6533 0.0056
-5.250 -0.4346 0.01103 0.00440 -0.0134 0.6503 0.0058
-5.000 -0.4082 0.01075 0.00406 -0.0131 0.6472 0.0061
-4.750 -0.3819 0.01044 0.00368 -0.0127 0.6443 0.0065
-4.500 -0.3555 0.01016 0.00335 -0.0124 0.6417 0.0072
-4.250 -0.3287 0.00992 0.00309 -0.0122 0.6392 0.0083
-4.000 -0.3016 0.00971 0.00286 -0.0120 0.6364 0.0093
-3.750 -0.2747 0.00949 0.00264 -0.0118 0.6335 0.0124
-3.500 -0.2478 0.00928 0.00244 -0.0117 0.6308 0.0173
-3.250 -0.2206 0.00912 0.00226 -0.0115 0.6282 0.0217
-3.000 -0.1935 0.00894 0.00210 -0.0114 0.6257 0.0289
-2.750 -0.1665 0.00874 0.00194 -0.0112 0.6231 0.0418
-2.500 -0.1396 0.00852 0.00180 -0.0111 0.6204 0.0626
-2.250 -0.1132 0.00825 0.00166 -0.0109 0.6176 0.0980
-2.000 -0.0864 0.00806 0.00155 -0.0107 0.6149 0.1277
-1.500 -0.0332 0.00761 0.00136 -0.0104 0.6097 0.2086
-1.250 -0.0072 0.00732 0.00127 -0.0101 0.6068 0.2731
-1.000 0.0193 0.00711 0.00121 -0.0099 0.6037 0.3208
-0.750 0.0455 0.00689 0.00114 -0.0097 0.6005 0.3776
-0.500 0.0717 0.00668 0.00109 -0.0094 0.5973 0.4340
-0.250 0.0964 0.00635 0.00105 -0.0089 0.5935 0.5234
0.000 0.1209 0.00606 0.00101 -0.0083 0.5891 0.6026
0.250 0.1448 0.00581 0.00098 -0.0075 0.5851 0.6780
0.500 0.1676 0.00553 0.00096 -0.0064 0.5815 0.7576
0.750 0.1904 0.00523 0.00097 -0.0051 0.5774 0.8425
1.000 0.2378 0.00518 0.00114 -0.0092 0.5719 0.9221
1.250 0.2786 0.00530 0.00124 -0.0120 0.5664 0.9424
1.500 0.3101 0.00539 0.00131 -0.0127 0.5606 0.9516
1.750 0.3370 0.00548 0.00137 -0.0124 0.5552 0.9592
2.000 0.3715 0.00556 0.00144 -0.0139 0.5490 0.9637
2.250 0.3944 0.00568 0.00152 -0.0127 0.5419 0.9707
2.500 0.4338 0.00576 0.00158 -0.0153 0.5325 0.9726
2.750 0.4714 0.00586 0.00165 -0.0175 0.5232 0.9748
3.000 0.5067 0.00598 0.00173 -0.0192 0.5126 0.9776
3.250 0.5385 0.00611 0.00182 -0.0202 0.4995 0.9812
3.500 0.5694 0.00626 0.00192 -0.0209 0.4824 0.9840
3.750 0.6054 0.00641 0.00200 -0.0229 0.4610 0.9852
4.000 0.6391 0.00663 0.00211 -0.0245 0.4317 0.9865
4.250 0.6713 0.00690 0.00226 -0.0257 0.3991 0.9879
4.500 0.7021 0.00721 0.00243 -0.0267 0.3656 0.9894
4.750 0.7313 0.00753 0.00263 -0.0274 0.3330 0.9909
5.000 0.7591 0.00793 0.00286 -0.0279 0.2951 0.9923
5.250 0.7859 0.00836 0.00312 -0.0281 0.2581 0.9936
5.500 0.8139 0.00864 0.00334 -0.0285 0.2360 0.9945
5.750 0.8431 0.00901 0.00358 -0.0293 0.2073 0.9952
6.000 0.8706 0.00955 0.00391 -0.0299 0.1661 0.9961
6.250 0.8983 0.00999 0.00422 -0.0305 0.1383 0.9970
6.500 0.9259 0.01038 0.00453 -0.0309 0.1180 0.9979
6.750 0.9527 0.01087 0.00489 -0.0314 0.0937 0.9988
7.000 0.9798 0.01126 0.00522 -0.0317 0.0787 0.9995
7.250 1.0052 0.01166 0.00557 -0.0318 0.0654 1.0000
7.500 1.0256 0.01207 0.00593 -0.0307 0.0550 1.0000
7.750 1.0453 0.01250 0.00632 -0.0296 0.0452 1.0000
8.000 1.0643 0.01295 0.00674 -0.0283 0.0364 1.0000
8.250 1.0833 0.01337 0.00715 -0.0270 0.0298 1.0000
8.500 1.1009 0.01385 0.00761 -0.0255 0.0230 1.0000
8.750 1.1177 0.01435 0.00808 -0.0239 0.0180 1.0000
9.000 1.1336 0.01486 0.00858 -0.0222 0.0148 1.0000
9.250 1.1497 0.01531 0.00906 -0.0204 0.0130 1.0000
9.500 1.1647 0.01577 0.00955 -0.0185 0.0118 1.0000
9.750 1.1777 0.01630 0.01010 -0.0163 0.0106 1.0000
10.000 1.1895 0.01683 0.01067 -0.0139 0.0099 1.0000
10.250 1.1991 0.01731 0.01119 -0.0111 0.0094 1.0000
10.500 1.2016 0.01778 0.01171 -0.0070 0.0091 1.0000
10.750 1.2066 0.01835 0.01233 -0.0038 0.0086 1.0000
11.000 1.2132 0.01905 0.01309 -0.0012 0.0083 1.0000
11.250 1.2213 0.01983 0.01391 0.0010 0.0079 1.0000
11.500 1.2296 0.02071 0.01484 0.0029 0.0072 1.0000
11.750 1.2372 0.02174 0.01591 0.0047 0.0066 1.0000
12.000 1.2482 0.02262 0.01684 0.0060 0.0063 1.0000
12.250 1.2584 0.02360 0.01788 0.0073 0.0060 1.0000
12.500 1.2687 0.02463 0.01895 0.0085 0.0053 1.0000
12.750 1.2778 0.02579 0.02016 0.0096 0.0049 1.0000
13.000 1.2857 0.02708 0.02147 0.0108 0.0042 1.0000
13.250 1.2938 0.02840 0.02287 0.0118 0.0041 1.0000
13.500 1.3025 0.02969 0.02420 0.0127 0.0036 1.0000
13.750 1.3099 0.03111 0.02570 0.0136 0.0034 1.0000
14.000 1.3159 0.03270 0.02735 0.0144 0.0032 1.0000
14.250 1.3203 0.03445 0.02915 0.0152 0.0028 1.0000
14.500 1.3242 0.03629 0.03106 0.0160 0.0026 1.0000
14.750 1.3298 0.03802 0.03287 0.0166 0.0025 1.0000
15.000 1.3327 0.04002 0.03495 0.0171 0.0025 1.0000
15.250 1.3357 0.04206 0.03708 0.0176 0.0024 1.0000
15.500 1.3382 0.04427 0.03936 0.0179 0.0022 1.0000
15.750 1.3398 0.04662 0.04181 0.0181 0.0022 1.0000
16.000 1.3406 0.04913 0.04440 0.0182 0.0021 1.0000
16.250 1.3414 0.05174 0.04709 0.0182 0.0020 1.0000
16.500 1.3392 0.05477 0.05021 0.0180 0.0019 1.0000
16.750 1.3372 0.05785 0.05339 0.0176 0.0018 1.0000
17.000 1.3331 0.06131 0.05694 0.0170 0.0017 1.0000
17.250 1.3284 0.06496 0.06070 0.0163 0.0017 1.0000
17.500 1.3251 0.06849 0.06434 0.0155 0.0017 1.0000
17.750 1.3160 0.07296 0.06892 0.0143 0.0017 1.0000
18.000 1.3063 0.07767 0.07375 0.0128 0.0016 1.0000
18.250 1.2933 0.08298 0.07917 0.0111 0.0015 1.0000
18.500 1.2849 0.08771 0.08401 0.0094 0.0016 1.0000
18.750 1.2763 0.09258 0.08899 0.0075 0.0016 1.0000
19.000 1.2591 0.09899 0.09553 0.0049 0.0015 1.0000
19.250 1.2348 0.10683 0.10352 0.0016 0.0015 1.0000
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Polar data table (+)
Polar graphs
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