EPPLER 266 AIRFOIL (e266-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: EPPLER 266 AIRFOIL (e266-il) Reynolds number: 200,000 Max Cl/Cd: 59.64 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e266-il-200000-n5.txt Download as CSV file: xf-e266-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3375 0.07130 0.06655 -0.1033 0.7493 0.0149
-12.000 -0.3512 0.06596 0.06112 -0.1067 0.7429 0.0148
-11.750 -0.3768 0.06012 0.05509 -0.1093 0.7377 0.0147
-11.500 -0.3962 0.05598 0.05078 -0.1100 0.7326 0.0146
-11.250 -0.4175 0.05212 0.04672 -0.1094 0.7275 0.0145
-11.000 -0.4370 0.04876 0.04312 -0.1078 0.7228 0.0145
-10.500 -0.4631 0.04349 0.03740 -0.1028 0.7143 0.0144
-10.250 -0.4742 0.04101 0.03466 -0.0996 0.7101 0.0144
-10.000 -0.4831 0.03877 0.03212 -0.0960 0.7061 0.0145
-9.750 -0.4905 0.03676 0.02975 -0.0919 0.7028 0.0146
-9.500 -0.4881 0.03495 0.02767 -0.0890 0.6994 0.0146
-9.250 -0.4840 0.03314 0.02545 -0.0862 0.6961 0.0149
-9.000 -0.4735 0.03142 0.02353 -0.0844 0.6930 0.0154
-8.750 -0.4584 0.03025 0.02222 -0.0832 0.6902 0.0158
-8.500 -0.4413 0.02888 0.02061 -0.0820 0.6877 0.0160
-8.000 -0.3998 0.02623 0.01754 -0.0805 0.6830 0.0164
-7.750 -0.3765 0.02508 0.01623 -0.0801 0.6805 0.0166
-7.500 -0.3524 0.02402 0.01504 -0.0798 0.6780 0.0169
-7.250 -0.3282 0.02309 0.01400 -0.0795 0.6756 0.0172
-7.000 -0.3045 0.02220 0.01299 -0.0790 0.6733 0.0176
-6.750 -0.2820 0.02146 0.01214 -0.0784 0.6712 0.0181
-6.500 -0.2606 0.02080 0.01137 -0.0775 0.6693 0.0185
-6.250 -0.2408 0.02016 0.01070 -0.0765 0.6672 0.0190
-6.000 -0.2222 0.01956 0.01011 -0.0753 0.6651 0.0198
-5.750 -0.2023 0.01912 0.00964 -0.0743 0.6631 0.0212
-5.500 -0.1824 0.01869 0.00915 -0.0732 0.6611 0.0224
-5.250 -0.1626 0.01827 0.00866 -0.0721 0.6592 0.0234
-5.000 -0.1427 0.01784 0.00819 -0.0710 0.6575 0.0248
-4.750 -0.1215 0.01751 0.00778 -0.0700 0.6558 0.0267
-4.500 -0.1004 0.01716 0.00739 -0.0690 0.6542 0.0301
-4.250 -0.0795 0.01681 0.00704 -0.0681 0.6526 0.0388
-4.000 -0.0622 0.01626 0.00673 -0.0666 0.6506 0.0782
-3.750 -0.0464 0.01565 0.00646 -0.0650 0.6488 0.1511
-3.500 -0.0344 0.01484 0.00618 -0.0629 0.6471 0.2680
-3.250 -0.0282 0.01379 0.00588 -0.0597 0.6454 0.4339
-3.000 -0.0186 0.01335 0.00656 -0.0553 0.6438 0.6553
-2.750 0.0065 0.01406 0.00735 -0.0537 0.6422 0.7338
-2.500 0.0313 0.01459 0.00779 -0.0525 0.6406 0.7599
-2.250 0.0573 0.01504 0.00814 -0.0517 0.6390 0.7745
-2.000 0.0831 0.01554 0.00854 -0.0507 0.6376 0.7884
-1.750 0.1131 0.01610 0.00903 -0.0503 0.6364 0.7954
-1.500 0.1352 0.01620 0.00907 -0.0494 0.6348 0.8043
-1.250 0.1625 0.01642 0.00926 -0.0491 0.6331 0.8073
-1.000 0.1885 0.01655 0.00935 -0.0488 0.6313 0.8108
-0.750 0.2131 0.01658 0.00932 -0.0484 0.6293 0.8151
-0.500 0.2363 0.01652 0.00919 -0.0481 0.6275 0.8201
-0.250 0.2631 0.01659 0.00922 -0.0480 0.6260 0.8219
0.000 0.2898 0.01665 0.00923 -0.0480 0.6246 0.8239
0.250 0.3165 0.01669 0.00922 -0.0480 0.6232 0.8262
0.500 0.3432 0.01671 0.00918 -0.0481 0.6218 0.8287
0.750 0.3699 0.01673 0.00912 -0.0482 0.6205 0.8314
1.000 0.3927 0.01674 0.00914 -0.0479 0.6186 0.8348
1.250 0.4167 0.01680 0.00922 -0.0476 0.6167 0.8366
1.500 0.4413 0.01687 0.00932 -0.0472 0.6146 0.8381
1.750 0.4662 0.01694 0.00940 -0.0470 0.6126 0.8398
2.000 0.4917 0.01700 0.00946 -0.0469 0.6108 0.8414
2.250 0.5175 0.01705 0.00951 -0.0469 0.6091 0.8432
2.500 0.5440 0.01709 0.00954 -0.0470 0.6075 0.8453
2.750 0.5714 0.01712 0.00954 -0.0474 0.6060 0.8472
3.000 0.5995 0.01716 0.00957 -0.0479 0.6046 0.8489
3.250 0.6222 0.01728 0.00975 -0.0475 0.6023 0.8510
3.500 0.6437 0.01742 0.00997 -0.0467 0.5996 0.8524
3.750 0.6670 0.01754 0.01016 -0.0462 0.5970 0.8539
4.000 0.6918 0.01761 0.01027 -0.0460 0.5946 0.8552
4.250 0.7179 0.01765 0.01033 -0.0461 0.5924 0.8565
4.500 0.7459 0.01765 0.01036 -0.0464 0.5903 0.8579
4.750 0.7755 0.01765 0.01034 -0.0471 0.5885 0.8592
5.000 0.7920 0.01786 0.01070 -0.0455 0.5843 0.8616
5.250 0.8139 0.01796 0.01087 -0.0449 0.5805 0.8638
5.500 0.8396 0.01796 0.01092 -0.0449 0.5773 0.8654
5.750 0.8680 0.01788 0.01087 -0.0453 0.5746 0.8665
6.000 0.8932 0.01787 0.01092 -0.0450 0.5713 0.8677
6.250 0.9081 0.01804 0.01125 -0.0431 0.5661 0.8693
6.500 0.9311 0.01802 0.01130 -0.0424 0.5619 0.8708
6.750 0.9597 0.01786 0.01117 -0.0427 0.5584 0.8722
7.000 0.9745 0.01799 0.01144 -0.0408 0.5527 0.8746
7.250 0.9935 0.01796 0.01151 -0.0394 0.5467 0.8769
7.500 1.0220 0.01773 0.01130 -0.0397 0.5421 0.8784
7.750 1.0292 0.01798 0.01172 -0.0365 0.5341 0.8809
8.000 1.0514 0.01780 0.01161 -0.0356 0.5280 0.8824
8.250 1.0544 0.01800 0.01196 -0.0314 0.5194 0.8848
8.500 1.0693 0.01793 0.01195 -0.0293 0.5112 0.8870
8.750 1.0753 0.01816 0.01227 -0.0258 0.5002 0.8902
9.000 1.0820 0.01848 0.01269 -0.0226 0.4883 0.8935
9.250 1.0915 0.01876 0.01302 -0.0201 0.4739 0.8964
9.500 1.1006 0.01902 0.01326 -0.0174 0.4559 0.8989
9.750 1.1045 0.01955 0.01373 -0.0142 0.4312 0.9020
10.000 1.1025 0.02050 0.01451 -0.0107 0.3995 0.9057
10.250 1.0953 0.02198 0.01581 -0.0070 0.3681 0.9098
10.500 1.0842 0.02394 0.01760 -0.0036 0.3361 0.9139
10.750 1.0794 0.02581 0.01938 -0.0012 0.3116 0.9184
11.000 1.0694 0.02816 0.02157 0.0012 0.2815 0.9233
11.250 1.0644 0.03041 0.02371 0.0029 0.2563 0.9273
11.500 1.0574 0.03297 0.02613 0.0043 0.2264 0.9317
11.750 1.0580 0.03508 0.02817 0.0051 0.2044 0.9362
12.000 1.0603 0.03736 0.03039 0.0053 0.1829 0.9402
12.250 1.0644 0.03971 0.03267 0.0050 0.1601 0.9448
12.500 1.0683 0.04232 0.03520 0.0043 0.1357 0.9499
12.750 1.0744 0.04496 0.03775 0.0032 0.1133 0.9558
13.000 1.0799 0.04716 0.03992 0.0025 0.0953 0.9870
13.250 1.0785 0.04925 0.04193 0.0041 0.0819 1.0000
13.500 1.0813 0.05155 0.04417 0.0044 0.0677 1.0000
13.750 1.0840 0.05392 0.04649 0.0046 0.0553 1.0000
14.000 1.0876 0.05626 0.04881 0.0047 0.0446 1.0000
14.250 1.0896 0.05880 0.05132 0.0048 0.0343 1.0000
14.500 1.0920 0.06135 0.05387 0.0048 0.0276 1.0000
14.750 1.0937 0.06405 0.05658 0.0048 0.0226 1.0000
15.000 1.0969 0.06665 0.05922 0.0047 0.0206 1.0000
15.250 1.0990 0.06941 0.06205 0.0045 0.0181 1.0000
15.500 1.1027 0.07203 0.06475 0.0042 0.0173 1.0000
15.750 1.1035 0.07506 0.06785 0.0038 0.0162 1.0000
16.000 1.1062 0.07792 0.07082 0.0034 0.0156 1.0000
16.250 1.1080 0.08092 0.07393 0.0028 0.0146 1.0000
16.500 1.1089 0.08409 0.07720 0.0022 0.0142 1.0000
16.750 1.1084 0.08748 0.08069 0.0015 0.0137 1.0000
17.000 1.1066 0.09112 0.08442 0.0006 0.0135 1.0000
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Polar data table (+)
Polar graphs
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