EPPLER 266 AIRFOIL (e266-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 266 AIRFOIL (e266-il) Reynolds number: 500,000 Max Cl/Cd: 99.98 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e266-il-500000-n5.txt Download as CSV file: xf-e266-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3749 0.07685 0.07302 -0.0971 0.6867 0.0085
-12.750 -0.4666 0.05285 0.04857 -0.1117 0.6833 0.0083
-12.500 -0.4849 0.04881 0.04438 -0.1122 0.6798 0.0082
-12.250 -0.5135 0.04419 0.03950 -0.1113 0.6766 0.0083
-12.000 -0.5255 0.04152 0.03665 -0.1098 0.6728 0.0082
-11.500 -0.5544 0.03587 0.03052 -0.1046 0.6667 0.0082
-11.250 -0.5631 0.03350 0.02789 -0.1016 0.6635 0.0083
-11.000 -0.5649 0.03170 0.02586 -0.0989 0.6604 0.0084
-10.750 -0.5637 0.03008 0.02403 -0.0963 0.6576 0.0085
-10.500 -0.5601 0.02854 0.02226 -0.0938 0.6550 0.0085
-10.250 -0.5536 0.02713 0.02063 -0.0914 0.6526 0.0086
-10.000 -0.5444 0.02608 0.01939 -0.0892 0.6504 0.0087
-9.750 -0.5339 0.02518 0.01831 -0.0870 0.6481 0.0088
-9.500 -0.5197 0.02408 0.01706 -0.0854 0.6459 0.0088
-9.250 -0.5035 0.02285 0.01567 -0.0841 0.6437 0.0090
-9.000 -0.4852 0.02169 0.01439 -0.0832 0.6416 0.0092
-8.750 -0.4674 0.02093 0.01355 -0.0820 0.6397 0.0094
-8.500 -0.4483 0.02019 0.01271 -0.0810 0.6378 0.0094
-8.250 -0.4293 0.01955 0.01199 -0.0798 0.6361 0.0096
-8.000 -0.4103 0.01906 0.01146 -0.0787 0.6344 0.0099
-7.750 -0.3903 0.01846 0.01079 -0.0777 0.6325 0.0101
-7.500 -0.3700 0.01793 0.01021 -0.0767 0.6305 0.0104
-7.250 -0.3495 0.01742 0.00964 -0.0758 0.6287 0.0106
-7.000 -0.3291 0.01691 0.00906 -0.0748 0.6270 0.0110
-6.750 -0.3088 0.01642 0.00852 -0.0738 0.6255 0.0112
-6.500 -0.2888 0.01596 0.00799 -0.0727 0.6240 0.0114
-6.250 -0.2681 0.01557 0.00754 -0.0717 0.6225 0.0116
-6.000 -0.2476 0.01517 0.00710 -0.0706 0.6211 0.0118
-5.750 -0.2285 0.01466 0.00655 -0.0694 0.6198 0.0122
-5.500 -0.2072 0.01429 0.00616 -0.0685 0.6186 0.0126
-5.250 -0.1851 0.01396 0.00582 -0.0677 0.6172 0.0129
-5.000 -0.1625 0.01367 0.00551 -0.0670 0.6158 0.0135
-4.750 -0.1393 0.01341 0.00522 -0.0664 0.6142 0.0141
-4.500 -0.1157 0.01319 0.00495 -0.0658 0.6126 0.0149
-4.250 -0.0924 0.01293 0.00468 -0.0652 0.6112 0.0160
-4.000 -0.0685 0.01272 0.00444 -0.0647 0.6099 0.0176
-3.750 -0.0443 0.01252 0.00422 -0.0642 0.6087 0.0200
-3.500 -0.0211 0.01226 0.00401 -0.0636 0.6075 0.0320
-3.250 0.0013 0.01194 0.00382 -0.0629 0.6063 0.0654
-3.000 0.0219 0.01150 0.00362 -0.0620 0.6051 0.1299
-2.750 0.0399 0.01089 0.00341 -0.0608 0.6039 0.2338
-2.500 0.0571 0.01023 0.00319 -0.0594 0.6027 0.3508
-2.250 0.0717 0.00941 0.00291 -0.0575 0.6013 0.4944
-2.000 0.0838 0.00865 0.00288 -0.0546 0.6001 0.6677
-1.750 0.1090 0.00877 0.00316 -0.0539 0.5989 0.7314
-1.500 0.1362 0.00894 0.00330 -0.0537 0.5976 0.7552
-1.250 0.1639 0.00915 0.00351 -0.0536 0.5963 0.7686
-1.000 0.1918 0.00933 0.00368 -0.0535 0.5949 0.7765
-0.750 0.2199 0.00947 0.00378 -0.0536 0.5936 0.7827
-0.500 0.2477 0.00954 0.00378 -0.0538 0.5923 0.7877
0.000 0.3047 0.00969 0.00387 -0.0543 0.5901 0.7916
0.250 0.3333 0.00977 0.00391 -0.0546 0.5887 0.7934
0.500 0.3615 0.00981 0.00393 -0.0549 0.5875 0.7951
0.750 0.3895 0.00983 0.00395 -0.0552 0.5863 0.7967
1.000 0.4175 0.00986 0.00397 -0.0555 0.5850 0.7984
1.250 0.4456 0.00988 0.00398 -0.0558 0.5836 0.7999
1.500 0.4735 0.00990 0.00399 -0.0561 0.5820 0.8015
1.750 0.5015 0.00993 0.00400 -0.0564 0.5806 0.8030
2.000 0.5296 0.00995 0.00402 -0.0568 0.5792 0.8040
2.250 0.5576 0.00998 0.00406 -0.0570 0.5777 0.8049
2.500 0.5856 0.01002 0.00410 -0.0573 0.5762 0.8059
2.750 0.6137 0.01008 0.00416 -0.0576 0.5749 0.8069
3.000 0.6420 0.01015 0.00422 -0.0580 0.5734 0.8080
3.250 0.6696 0.01020 0.00430 -0.0582 0.5717 0.8090
3.500 0.6965 0.01023 0.00438 -0.0583 0.5697 0.8101
3.750 0.7234 0.01026 0.00444 -0.0584 0.5672 0.8112
4.000 0.7503 0.01027 0.00449 -0.0585 0.5643 0.8124
4.250 0.7772 0.01029 0.00453 -0.0586 0.5616 0.8136
4.500 0.8044 0.01032 0.00456 -0.0587 0.5590 0.8150
4.750 0.8311 0.01036 0.00462 -0.0588 0.5560 0.8165
5.000 0.8568 0.01038 0.00471 -0.0587 0.5524 0.8177
5.250 0.8829 0.01041 0.00477 -0.0586 0.5488 0.8189
5.500 0.9089 0.01043 0.00482 -0.0586 0.5453 0.8199
5.750 0.9346 0.01045 0.00487 -0.0584 0.5414 0.8209
6.000 0.9591 0.01048 0.00499 -0.0581 0.5358 0.8218
6.250 0.9836 0.01050 0.00505 -0.0576 0.5301 0.8229
6.500 1.0079 0.01055 0.00515 -0.0572 0.5247 0.8240
6.750 1.0315 0.01059 0.00527 -0.0567 0.5175 0.8252
7.000 1.0540 0.01066 0.00537 -0.0559 0.5093 0.8267
7.250 1.0728 0.01073 0.00544 -0.0544 0.4920 0.8283
7.500 1.0888 0.01090 0.00557 -0.0524 0.4721 0.8299
7.750 1.0969 0.01121 0.00578 -0.0489 0.4446 0.8317
8.000 1.0963 0.01169 0.00612 -0.0437 0.4141 0.8338
8.250 1.0915 0.01245 0.00671 -0.0382 0.3810 0.8359
8.500 1.0827 0.01340 0.00751 -0.0322 0.3466 0.8379
8.750 1.0760 0.01441 0.00842 -0.0270 0.3182 0.8400
9.000 1.0654 0.01572 0.00961 -0.0217 0.2880 0.8428
9.250 1.0591 0.01709 0.01089 -0.0175 0.2627 0.8454
9.500 1.0530 0.01866 0.01238 -0.0139 0.2398 0.8479
9.750 1.0430 0.02068 0.01425 -0.0104 0.2113 0.8503
10.000 1.0456 0.02210 0.01565 -0.0083 0.1969 0.8521
10.250 1.0365 0.02428 0.01771 -0.0054 0.1682 0.8542
10.500 1.0378 0.02590 0.01929 -0.0035 0.1516 0.8562
10.750 1.0429 0.02732 0.02070 -0.0020 0.1406 0.8582
11.000 1.0427 0.02912 0.02243 -0.0002 0.1217 0.8604
11.250 1.0427 0.03094 0.02417 0.0014 0.1038 0.8627
11.500 1.0439 0.03274 0.02589 0.0029 0.0880 0.8649
11.750 1.0476 0.03440 0.02752 0.0041 0.0753 0.8670
12.000 1.0514 0.03610 0.02918 0.0052 0.0625 0.8690
12.250 1.0537 0.03797 0.03100 0.0063 0.0489 0.8710
12.500 1.0564 0.03986 0.03284 0.0073 0.0368 0.8731
12.750 1.0603 0.04173 0.03469 0.0081 0.0271 0.8753
13.000 1.0632 0.04372 0.03664 0.0089 0.0174 0.8775
13.250 1.0683 0.04561 0.03852 0.0095 0.0132 0.8797
13.500 1.0756 0.04733 0.04029 0.0100 0.0114 0.8818
13.750 1.0829 0.04909 0.04210 0.0104 0.0105 0.8840
14.000 1.0916 0.05075 0.04384 0.0106 0.0102 0.8865
14.250 1.0997 0.05248 0.04565 0.0109 0.0095 0.8892
14.500 1.1074 0.05429 0.04754 0.0111 0.0092 0.8922
14.750 1.1132 0.05637 0.04968 0.0112 0.0086 0.8953
15.000 1.1222 0.05820 0.05160 0.0111 0.0087 0.8984
15.250 1.1239 0.06083 0.05431 0.0111 0.0080 0.9016
15.500 1.1319 0.06287 0.05643 0.0108 0.0080 0.9053
15.750 1.1374 0.06526 0.05893 0.0105 0.0078 0.9090
16.000 1.1441 0.06761 0.06136 0.0100 0.0077 0.9126
16.250 1.1506 0.07021 0.06407 0.0091 0.0075 0.9164
16.500 1.1571 0.07285 0.06679 0.0082 0.0073 0.9206
16.750 1.1605 0.07582 0.06987 0.0074 0.0072 0.9250
17.000 1.1683 0.07869 0.07283 0.0058 0.0069 0.9289
17.250 1.1716 0.08216 0.07641 0.0043 0.0069 0.9334
17.500 1.1772 0.08552 0.07988 0.0024 0.0068 0.9380
17.750 1.1827 0.08928 0.08376 -0.0001 0.0065 0.9422
18.000 1.1872 0.09332 0.08793 -0.0028 0.0065 0.9460
18.250 1.1890 0.09790 0.09262 -0.0058 0.0062 0.9511
18.500 1.1871 0.10247 0.09730 -0.0084 0.0061 0.9725
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