EPPLER 266 AIRFOIL (e266-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 266 AIRFOIL (e266-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.4 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e266-il-1000000.txt Download as CSV file: xf-e266-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 266 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.1922 0.09101 0.08806 -0.0848 0.6654 0.0153
-12.500 -0.2436 0.09340 0.09024 -0.0959 0.6744 0.0143
-9.500 -0.5388 0.02593 0.02056 -0.0837 0.6498 0.0114
-9.250 -0.5290 0.02382 0.01818 -0.0814 0.6477 0.0113
-9.000 -0.5141 0.02189 0.01600 -0.0798 0.6457 0.0112
-8.750 -0.4954 0.02068 0.01461 -0.0786 0.6435 0.0113
-8.500 -0.4746 0.01956 0.01333 -0.0778 0.6410 0.0113
-8.250 -0.4536 0.01893 0.01259 -0.0769 0.6397 0.0117
-8.000 -0.4304 0.01799 0.01154 -0.0764 0.6382 0.0117
-7.750 -0.4073 0.01727 0.01074 -0.0759 0.6366 0.0118
-7.500 -0.3843 0.01671 0.01011 -0.0753 0.6349 0.0119
-7.250 -0.3610 0.01607 0.00941 -0.0748 0.6332 0.0120
-7.000 -0.3383 0.01542 0.00870 -0.0741 0.6314 0.0122
-6.750 -0.3179 0.01455 0.00778 -0.0731 0.6297 0.0123
-6.500 -0.2985 0.01393 0.00711 -0.0719 0.6280 0.0125
-6.250 -0.2789 0.01343 0.00658 -0.0707 0.6261 0.0128
-6.000 -0.2577 0.01305 0.00617 -0.0698 0.6246 0.0131
-5.750 -0.2354 0.01272 0.00583 -0.0690 0.6236 0.0136
-5.500 -0.2131 0.01237 0.00547 -0.0683 0.6224 0.0141
-5.250 -0.1904 0.01205 0.00512 -0.0675 0.6212 0.0146
-5.000 -0.1672 0.01177 0.00481 -0.0669 0.6199 0.0150
-4.750 -0.1430 0.01154 0.00456 -0.0664 0.6185 0.0154
-4.500 -0.1209 0.01116 0.00414 -0.0655 0.6171 0.0163
-4.250 -0.0967 0.01092 0.00389 -0.0650 0.6157 0.0173
-4.000 -0.0718 0.01074 0.00368 -0.0647 0.6144 0.0185
-3.750 -0.0469 0.01055 0.00347 -0.0643 0.6130 0.0207
-3.500 -0.0226 0.01033 0.00329 -0.0638 0.6116 0.0306
-3.000 0.0146 0.00916 0.00287 -0.0614 0.6088 0.2222
-2.750 0.0314 0.00843 0.00264 -0.0598 0.6079 0.3558
-2.500 0.0442 0.00748 0.00234 -0.0576 0.6068 0.5341
-2.250 0.0595 0.00683 0.00225 -0.0553 0.6057 0.6845
-2.000 0.0861 0.00684 0.00233 -0.0551 0.6045 0.7255
-1.750 0.1141 0.00691 0.00241 -0.0552 0.6034 0.7438
-1.500 0.1424 0.00701 0.00249 -0.0553 0.6021 0.7571
-1.250 0.1706 0.00718 0.00263 -0.0553 0.6008 0.7696
-1.000 0.1994 0.00732 0.00279 -0.0555 0.5995 0.7769
-0.750 0.2281 0.00748 0.00291 -0.0557 0.5983 0.7835
-0.500 0.2567 0.00760 0.00303 -0.0559 0.5972 0.7885
-0.250 0.2859 0.00777 0.00319 -0.0562 0.5958 0.7927
0.000 0.3150 0.00796 0.00335 -0.0566 0.5940 0.7967
0.250 0.3437 0.00806 0.00342 -0.0570 0.5929 0.7998
0.500 0.3721 0.00807 0.00343 -0.0573 0.5920 0.8020
0.750 0.4006 0.00808 0.00345 -0.0576 0.5909 0.8037
1.000 0.4292 0.00810 0.00348 -0.0579 0.5897 0.8051
1.250 0.4578 0.00813 0.00351 -0.0583 0.5884 0.8064
1.500 0.4864 0.00816 0.00354 -0.0587 0.5870 0.8076
1.750 0.5150 0.00818 0.00356 -0.0590 0.5856 0.8089
2.000 0.5436 0.00820 0.00357 -0.0594 0.5842 0.8101
2.250 0.5722 0.00823 0.00359 -0.0598 0.5828 0.8114
2.500 0.6007 0.00826 0.00361 -0.0603 0.5812 0.8127
2.750 0.6295 0.00835 0.00367 -0.0608 0.5792 0.8138
3.000 0.6578 0.00840 0.00372 -0.0611 0.5772 0.8149
3.250 0.6853 0.00837 0.00372 -0.0613 0.5753 0.8158
3.500 0.7131 0.00837 0.00374 -0.0616 0.5731 0.8168
3.750 0.7405 0.00832 0.00371 -0.0618 0.5707 0.8180
4.000 0.7681 0.00829 0.00369 -0.0620 0.5683 0.8191
4.250 0.7958 0.00829 0.00370 -0.0622 0.5658 0.8200
4.500 0.8241 0.00838 0.00377 -0.0626 0.5630 0.8209
4.750 0.8509 0.00837 0.00381 -0.0626 0.5608 0.8219
5.000 0.8776 0.00834 0.00384 -0.0626 0.5579 0.8229
5.250 0.9042 0.00832 0.00385 -0.0627 0.5543 0.8240
5.500 0.9309 0.00832 0.00387 -0.0627 0.5510 0.8252
5.750 0.9579 0.00839 0.00393 -0.0628 0.5474 0.8265
6.000 0.9838 0.00837 0.00398 -0.0627 0.5439 0.8277
6.250 1.0097 0.00835 0.00401 -0.0626 0.5392 0.8288
6.500 1.0348 0.00838 0.00404 -0.0623 0.5339 0.8300
6.750 1.0602 0.00838 0.00409 -0.0621 0.5271 0.8310
7.000 1.0834 0.00843 0.00412 -0.0615 0.5180 0.8320
7.250 1.1070 0.00846 0.00418 -0.0609 0.5058 0.8330
7.500 1.1261 0.00857 0.00425 -0.0595 0.4844 0.8345
7.750 1.1404 0.00885 0.00444 -0.0571 0.4568 0.8360
8.000 1.1509 0.00924 0.00473 -0.0541 0.4284 0.8377
8.250 1.1515 0.00976 0.00510 -0.0491 0.3939 0.8396
8.500 1.1496 0.01045 0.00564 -0.0438 0.3596 0.8417
8.750 1.1449 0.01127 0.00630 -0.0383 0.3255 0.8439
9.000 1.1455 0.01199 0.00691 -0.0339 0.2994 0.8459
9.250 1.1399 0.01295 0.00773 -0.0287 0.2699 0.8477
9.500 1.1380 0.01384 0.00855 -0.0245 0.2491 0.8500
9.750 1.1298 0.01511 0.00971 -0.0197 0.2222 0.8525
10.000 1.1265 0.01639 0.01094 -0.0160 0.2023 0.8550
10.250 1.1204 0.01801 0.01247 -0.0125 0.1795 0.8575
10.500 1.1163 0.01969 0.01407 -0.0095 0.1590 0.8599
10.750 1.1148 0.02135 0.01565 -0.0071 0.1410 0.8619
11.000 1.1122 0.02315 0.01737 -0.0047 0.1229 0.8638
11.250 1.1099 0.02497 0.01912 -0.0025 0.1040 0.8664
11.500 1.1077 0.02683 0.02091 -0.0004 0.0863 0.8687
11.750 1.1099 0.02846 0.02250 0.0011 0.0741 0.8709
12.000 1.1128 0.03009 0.02409 0.0026 0.0630 0.8731
12.250 1.1060 0.03243 0.02629 0.0047 0.0421 0.8756
12.500 1.1052 0.03444 0.02824 0.0061 0.0288 0.8778
12.750 1.1020 0.03673 0.03044 0.0076 0.0158 0.8803
13.000 1.1083 0.03835 0.03209 0.0084 0.0129 0.8828
13.250 1.1151 0.03998 0.03376 0.0091 0.0117 0.8852
13.500 1.1225 0.04157 0.03540 0.0098 0.0109 0.8876
13.750 1.1317 0.04306 0.03694 0.0102 0.0106 0.8901
14.000 1.1395 0.04470 0.03864 0.0107 0.0099 0.8926
14.250 1.1484 0.04627 0.04028 0.0110 0.0099 0.8952
14.500 1.1553 0.04806 0.04213 0.0114 0.0094 0.8982
14.750 1.1593 0.05011 0.04424 0.0119 0.0088 0.9014
15.000 1.1594 0.05260 0.04682 0.0124 0.0084 0.9047
15.250 1.1650 0.05460 0.04889 0.0127 0.0084 0.9081
15.500 1.1732 0.05645 0.05082 0.0127 0.0082 0.9119
15.750 1.1783 0.05864 0.05309 0.0127 0.0082 0.9164
16.000 1.1828 0.06087 0.05540 0.0128 0.0078 0.9213
16.250 1.1914 0.06295 0.05757 0.0122 0.0078 0.9262
16.500 1.1968 0.06551 0.06022 0.0116 0.0077 0.9319
16.750 1.2020 0.06856 0.06337 0.0102 0.0076 0.9376
17.000 1.2115 0.07172 0.06664 0.0079 0.0074 0.9426
17.250 1.2218 0.07507 0.07009 0.0051 0.0072 0.9463
17.500 1.2317 0.07877 0.07389 0.0020 0.0071 0.9501
17.750 1.2400 0.08272 0.07795 -0.0013 0.0070 0.9530
18.000 1.2464 0.08694 0.08226 -0.0045 0.0068 0.9554
18.250 1.2522 0.09116 0.08659 -0.0077 0.0068 0.9577
18.500 1.2546 0.09558 0.09111 -0.0106 0.0067 0.9672
18.750 1.2467 0.09971 0.09531 -0.0108 0.0066 1.0000
19.000 1.2425 0.10353 0.09920 -0.0116 0.0066 1.0000
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Polar data table (+)
Polar graphs
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