EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1211 AIRFOIL (e1211-il) Reynolds number: 200,000 Max Cl/Cd: 62.56 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1211-il-200000-n5.txt Download as CSV file: xf-e1211-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1211 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5901 0.09139 0.08656 -0.0505 1.0000 0.0432
-14.250 -0.6000 0.08655 0.08168 -0.0528 1.0000 0.0450
-14.000 -0.6094 0.08197 0.07712 -0.0551 1.0000 0.0465
-13.750 -0.6244 0.07669 0.07182 -0.0577 1.0000 0.0484
-13.500 -0.6431 0.07124 0.06633 -0.0605 1.0000 0.0499
-13.250 -0.6691 0.06516 0.06023 -0.0637 1.0000 0.0510
-13.000 -0.7031 0.05832 0.05334 -0.0673 1.0000 0.0518
-12.750 -0.7443 0.05098 0.04590 -0.0710 1.0000 0.0516
-12.500 -0.7971 0.04256 0.03734 -0.0752 1.0000 0.0506
-12.250 -0.8611 0.03364 0.02815 -0.0802 1.0000 0.0489
-12.000 -0.8740 0.03080 0.02519 -0.0795 1.0000 0.0504
-11.750 -0.8591 0.02853 0.02281 -0.0816 0.9955 0.0544
-11.500 -0.8298 0.02659 0.02076 -0.0852 0.9854 0.0597
-11.250 -0.8025 0.02509 0.01919 -0.0873 0.9715 0.0652
-11.000 -0.7764 0.02387 0.01790 -0.0885 0.9533 0.0704
-10.750 -0.7444 0.02280 0.01676 -0.0905 0.9367 0.0761
-10.500 -0.7055 0.02184 0.01571 -0.0935 0.9212 0.0825
-10.250 -0.6626 0.02099 0.01476 -0.0970 0.9038 0.0892
-10.000 -0.6185 0.02025 0.01388 -0.1006 0.8835 0.0959
-9.750 -0.5775 0.01965 0.01313 -0.1034 0.8594 0.1022
-9.500 -0.5439 0.01921 0.01257 -0.1047 0.8342 0.1074
-9.250 -0.5147 0.01886 0.01204 -0.1050 0.8107 0.1132
-9.000 -0.4877 0.01864 0.01172 -0.1048 0.7890 0.1190
-8.750 -0.4616 0.01845 0.01138 -0.1044 0.7696 0.1248
-8.250 -0.4103 0.01814 0.01080 -0.1034 0.7344 0.1351
-8.000 -0.3844 0.01803 0.01060 -0.1028 0.7189 0.1393
-7.750 -0.3587 0.01784 0.01020 -0.1022 0.7043 0.1437
-7.500 -0.3329 0.01766 0.00994 -0.1017 0.6898 0.1469
-7.250 -0.3067 0.01753 0.00974 -0.1012 0.6765 0.1503
-7.000 -0.2806 0.01739 0.00943 -0.1006 0.6639 0.1542
-6.750 -0.2542 0.01718 0.00908 -0.1001 0.6512 0.1579
-6.500 -0.2278 0.01707 0.00892 -0.0996 0.6397 0.1609
-6.250 -0.2011 0.01696 0.00872 -0.0992 0.6276 0.1644
-6.000 -0.1743 0.01683 0.00844 -0.0987 0.6168 0.1682
-5.750 -0.1475 0.01666 0.00815 -0.0983 0.6057 0.1716
-5.500 -0.1208 0.01654 0.00800 -0.0978 0.5955 0.1745
-5.250 -0.0937 0.01644 0.00783 -0.0974 0.5849 0.1779
-5.000 -0.0666 0.01634 0.00761 -0.0970 0.5755 0.1815
-4.750 -0.0393 0.01623 0.00734 -0.0966 0.5654 0.1849
-4.500 -0.0126 0.01608 0.00716 -0.0961 0.5563 0.1879
-4.250 0.0148 0.01598 0.00704 -0.0958 0.5468 0.1910
-4.000 0.0418 0.01592 0.00687 -0.0953 0.5382 0.1944
-3.750 0.0694 0.01582 0.00670 -0.0950 0.5293 0.1980
-3.500 0.0967 0.01576 0.00651 -0.0946 0.5205 0.2012
-3.250 0.1238 0.01562 0.00637 -0.0942 0.5126 0.2043
-3.000 0.1511 0.01555 0.00628 -0.0939 0.5042 0.2077
-2.500 0.2059 0.01545 0.00605 -0.0932 0.4884 0.2149
-2.250 0.2333 0.01543 0.00592 -0.0928 0.4806 0.2183
-2.000 0.2602 0.01534 0.00584 -0.0924 0.4738 0.2219
-1.750 0.2877 0.01529 0.00579 -0.0921 0.4663 0.2255
-1.500 0.3148 0.01528 0.00572 -0.0917 0.4592 0.2294
-1.250 0.3421 0.01528 0.00566 -0.0913 0.4522 0.2337
-1.000 0.3695 0.01526 0.00561 -0.0909 0.4451 0.2375
-0.750 0.3962 0.01524 0.00558 -0.0905 0.4388 0.2415
-0.500 0.4235 0.01524 0.00558 -0.0902 0.4326 0.2461
-0.250 0.4507 0.01526 0.00557 -0.0898 0.4258 0.2512
0.000 0.4775 0.01531 0.00555 -0.0894 0.4195 0.2559
0.250 0.5044 0.01530 0.00558 -0.0890 0.4136 0.2610
0.500 0.5315 0.01533 0.00562 -0.0887 0.4076 0.2668
0.750 0.5583 0.01540 0.00565 -0.0883 0.4018 0.2733
1.000 0.5848 0.01545 0.00570 -0.0878 0.3965 0.2800
1.250 0.6117 0.01549 0.00579 -0.0875 0.3905 0.2878
1.500 0.6383 0.01557 0.00585 -0.0871 0.3848 0.2958
1.750 0.6643 0.01565 0.00594 -0.0866 0.3801 0.3055
2.000 0.6912 0.01573 0.00605 -0.0862 0.3750 0.3173
2.250 0.7175 0.01579 0.00618 -0.0858 0.3695 0.3311
2.500 0.7434 0.01588 0.00630 -0.0853 0.3645 0.3468
2.750 0.7690 0.01600 0.00643 -0.0848 0.3601 0.3657
3.000 0.7954 0.01606 0.00662 -0.0844 0.3554 0.3903
3.250 0.8211 0.01613 0.00680 -0.0840 0.3506 0.4218
3.500 0.8461 0.01621 0.00698 -0.0834 0.3460 0.4602
3.750 0.8706 0.01631 0.00718 -0.0827 0.3420 0.5078
4.000 0.8954 0.01633 0.00743 -0.0820 0.3376 0.5674
4.250 0.9188 0.01632 0.00768 -0.0810 0.3335 0.6462
4.500 0.9389 0.01627 0.00792 -0.0792 0.3297 0.7503
4.750 0.9671 0.01616 0.00807 -0.0788 0.3257 1.0000
5.000 0.9922 0.01643 0.00831 -0.0782 0.3219 1.0000
5.250 1.0171 0.01668 0.00855 -0.0777 0.3177 1.0000
5.500 1.0414 0.01696 0.00880 -0.0770 0.3138 1.0000
5.750 1.0651 0.01727 0.00904 -0.0763 0.3104 1.0000
6.000 1.0885 0.01762 0.00930 -0.0756 0.3073 1.0000
6.250 1.1126 0.01790 0.00962 -0.0749 0.3038 1.0000
6.500 1.1360 0.01820 0.00994 -0.0742 0.3000 1.0000
6.750 1.1586 0.01852 0.01024 -0.0733 0.2964 1.0000
7.000 1.1806 0.01888 0.01055 -0.0724 0.2932 1.0000
7.250 1.2023 0.01928 0.01088 -0.0715 0.2903 1.0000
7.500 1.2243 0.01962 0.01127 -0.0706 0.2873 1.0000
7.750 1.2457 0.01998 0.01167 -0.0696 0.2842 1.0000
8.000 1.2661 0.02036 0.01207 -0.0685 0.2810 1.0000
8.250 1.2851 0.02075 0.01245 -0.0671 0.2780 1.0000
8.500 1.3028 0.02118 0.01283 -0.0656 0.2752 1.0000
8.750 1.3206 0.02163 0.01328 -0.0642 0.2726 1.0000
9.000 1.3379 0.02207 0.01379 -0.0627 0.2698 1.0000
9.250 1.3548 0.02255 0.01431 -0.0611 0.2671 1.0000
9.500 1.3710 0.02305 0.01485 -0.0596 0.2644 1.0000
9.750 1.3865 0.02358 0.01539 -0.0580 0.2619 1.0000
10.000 1.4018 0.02415 0.01594 -0.0565 0.2594 1.0000
10.250 1.4174 0.02477 0.01653 -0.0551 0.2570 1.0000
10.500 1.4309 0.02542 0.01729 -0.0535 0.2545 1.0000
10.750 1.4439 0.02613 0.01808 -0.0520 0.2518 1.0000
11.000 1.4567 0.02688 0.01889 -0.0505 0.2495 1.0000
11.250 1.4690 0.02768 0.01973 -0.0491 0.2471 1.0000
11.500 1.4814 0.02851 0.02058 -0.0478 0.2450 1.0000
11.750 1.4946 0.02936 0.02141 -0.0466 0.2429 1.0000
12.000 1.5058 0.03034 0.02244 -0.0454 0.2407 1.0000
12.250 1.5140 0.03151 0.02373 -0.0441 0.2383 1.0000
12.500 1.5221 0.03273 0.02505 -0.0430 0.2358 1.0000
12.750 1.5304 0.03400 0.02640 -0.0419 0.2336 1.0000
13.000 1.5388 0.03530 0.02775 -0.0410 0.2314 1.0000
13.250 1.5481 0.03657 0.02904 -0.0402 0.2292 1.0000
13.500 1.5597 0.03773 0.03018 -0.0395 0.2272 1.0000
13.750 1.5639 0.03949 0.03205 -0.0387 0.2251 1.0000
14.000 1.5657 0.04151 0.03421 -0.0381 0.2227 1.0000
14.250 1.5679 0.04357 0.03639 -0.0376 0.2204 1.0000
14.500 1.5701 0.04568 0.03858 -0.0372 0.2179 1.0000
14.750 1.5745 0.04762 0.04057 -0.0369 0.2156 1.0000
15.000 1.5825 0.04924 0.04219 -0.0366 0.2135 1.0000
15.250 1.5875 0.05123 0.04423 -0.0364 0.2114 1.0000
15.500 1.5784 0.05479 0.04797 -0.0367 0.2088 1.0000
15.750 1.5716 0.05824 0.05158 -0.0371 0.2062 1.0000
16.000 1.5673 0.06151 0.05495 -0.0376 0.2036 1.0000
16.250 1.5682 0.06422 0.05771 -0.0380 0.2012 1.0000
16.500 1.5778 0.06588 0.05935 -0.0380 0.1991 1.0000
16.750 1.5696 0.06988 0.06348 -0.0389 0.1966 1.0000
17.000 1.5445 0.07632 0.07014 -0.0410 0.1934 1.0000
17.250 1.5278 0.08183 0.07580 -0.0428 0.1903 1.0000
17.500 1.5252 0.08540 0.07944 -0.0439 0.1877 1.0000
17.750 1.5381 0.08672 0.08073 -0.0440 0.1857 1.0000
18.000 1.5045 0.09509 0.08931 -0.0473 0.1821 1.0000
18.250 1.4419 0.10843 0.10293 -0.0532 0.1766 1.0000
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Polar data table (+)
Polar graphs
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