EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1211 AIRFOIL (e1211-il) Reynolds number: 200,000 Max Cl/Cd: 58.39 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1211-il-200000.txt Download as CSV file: xf-e1211-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.3357 0.17392 0.16977 -0.0159 1.0000 0.0696
-15.750 -0.6898 0.08946 0.08455 -0.0591 1.0000 0.0495
-15.500 -0.6963 0.08519 0.08025 -0.0611 1.0000 0.0502
-15.250 -0.6664 0.08705 0.08231 -0.0587 1.0000 0.0516
-15.000 -0.6904 0.07992 0.07505 -0.0629 1.0000 0.0521
-14.750 -0.7106 0.07378 0.06879 -0.0664 1.0000 0.0530
-14.500 -0.7311 0.06796 0.06285 -0.0698 1.0000 0.0538
-14.250 -0.7525 0.06216 0.05690 -0.0732 1.0000 0.0546
-14.000 -0.7489 0.06020 0.05504 -0.0734 1.0000 0.0560
-13.750 -0.7551 0.05685 0.05172 -0.0747 1.0000 0.0574
-13.500 -0.7707 0.05226 0.04708 -0.0771 1.0000 0.0587
-13.250 -0.7913 0.04708 0.04177 -0.0800 1.0000 0.0600
-13.000 -0.8040 0.04330 0.03801 -0.0815 1.0000 0.0614
-12.750 -0.8192 0.03925 0.03396 -0.0834 1.0000 0.0626
-12.500 -0.8417 0.03512 0.02975 -0.0851 1.0000 0.0637
-12.250 -0.8658 0.03226 0.02677 -0.0839 1.0000 0.0651
-12.000 -0.8729 0.03032 0.02481 -0.0821 1.0000 0.0677
-11.750 -0.8743 0.02874 0.02318 -0.0803 1.0000 0.0716
-11.500 -0.8728 0.02746 0.02193 -0.0782 1.0000 0.0758
-11.250 -0.8706 0.02635 0.02078 -0.0759 1.0000 0.0810
-11.000 -0.8645 0.02554 0.01988 -0.0740 0.9994 0.0865
-10.750 -0.8187 0.02460 0.01890 -0.0789 0.9924 0.0956
-10.500 -0.7750 0.02391 0.01811 -0.0828 0.9838 0.1037
-10.250 -0.7309 0.02353 0.01777 -0.0863 0.9750 0.1105
-10.000 -0.6866 0.02318 0.01743 -0.0896 0.9659 0.1169
-9.750 -0.6474 0.02262 0.01671 -0.0921 0.9531 0.1236
-9.500 -0.6064 0.02256 0.01675 -0.0943 0.9407 0.1288
-9.250 -0.5635 0.02202 0.01606 -0.0973 0.9290 0.1350
-9.000 -0.5149 0.02211 0.01621 -0.1007 0.9176 0.1408
-8.750 -0.4708 0.02196 0.01597 -0.1036 0.9007 0.1473
-8.500 -0.4264 0.02241 0.01642 -0.1061 0.8808 0.1537
-8.250 -0.3920 0.02211 0.01592 -0.1072 0.8581 0.1592
-8.000 -0.3606 0.02243 0.01627 -0.1072 0.8352 0.1630
-7.750 -0.3345 0.02225 0.01586 -0.1067 0.8141 0.1678
-7.500 -0.3105 0.02170 0.01503 -0.1060 0.7952 0.1720
-7.250 -0.2841 0.02170 0.01506 -0.1053 0.7767 0.1751
-7.000 -0.2585 0.02164 0.01490 -0.1045 0.7596 0.1790
-6.750 -0.2339 0.02134 0.01432 -0.1039 0.7443 0.1838
-6.500 -0.2088 0.02086 0.01370 -0.1033 0.7301 0.1875
-6.250 -0.1826 0.02080 0.01365 -0.1026 0.7150 0.1909
-6.000 -0.1565 0.02067 0.01340 -0.1020 0.7019 0.1950
-5.750 -0.1308 0.02042 0.01289 -0.1014 0.6889 0.1997
-5.500 -0.1054 0.01989 0.01227 -0.1009 0.6762 0.2034
-5.250 -0.0785 0.01978 0.01211 -0.1004 0.6648 0.2070
-5.000 -0.0522 0.01959 0.01186 -0.0999 0.6524 0.2110
-4.750 -0.0254 0.01942 0.01145 -0.0994 0.6420 0.2155
-4.500 0.0006 0.01899 0.01090 -0.0990 0.6302 0.2195
-4.250 0.0276 0.01873 0.01059 -0.0986 0.6205 0.2231
-4.000 0.0543 0.01856 0.01042 -0.0981 0.6092 0.2270
-3.750 0.0817 0.01845 0.01011 -0.0977 0.5999 0.2315
-3.500 0.1086 0.01829 0.00983 -0.0973 0.5892 0.2355
-3.250 0.1355 0.01787 0.00932 -0.0969 0.5804 0.2396
-3.000 0.1624 0.01770 0.00918 -0.0965 0.5706 0.2435
-2.750 0.1897 0.01758 0.00896 -0.0961 0.5615 0.2478
-2.500 0.2172 0.01751 0.00878 -0.0958 0.5526 0.2524
-2.250 0.2445 0.01732 0.00848 -0.0954 0.5437 0.2565
-2.000 0.2718 0.01711 0.00823 -0.0951 0.5360 0.2608
-1.750 0.2987 0.01699 0.00814 -0.0947 0.5269 0.2655
-1.500 0.3264 0.01696 0.00798 -0.0943 0.5190 0.2706
-1.250 0.3539 0.01695 0.00788 -0.0940 0.5109 0.2750
-1.000 0.3808 0.01669 0.00765 -0.0936 0.5030 0.2801
-0.750 0.4086 0.01672 0.00759 -0.0934 0.4962 0.2856
-0.500 0.4354 0.01666 0.00756 -0.0929 0.4881 0.2913
-0.250 0.4629 0.01665 0.00744 -0.0926 0.4807 0.2967
0.000 0.4900 0.01657 0.00738 -0.0923 0.4741 0.3033
0.250 0.5168 0.01655 0.00741 -0.0918 0.4668 0.3104
0.500 0.5444 0.01660 0.00735 -0.0915 0.4602 0.3174
0.750 0.5714 0.01657 0.00737 -0.0912 0.4539 0.3255
1.000 0.5979 0.01658 0.00742 -0.0907 0.4468 0.3351
1.250 0.6249 0.01655 0.00741 -0.0903 0.4407 0.3454
1.500 0.6524 0.01669 0.00750 -0.0901 0.4351 0.3579
1.750 0.6783 0.01665 0.00761 -0.0896 0.4287 0.3719
2.000 0.7049 0.01665 0.00766 -0.0892 0.4227 0.3905
2.250 0.7325 0.01677 0.00778 -0.0890 0.4174 0.4158
2.500 0.7576 0.01674 0.00798 -0.0884 0.4117 0.4509
2.750 0.7829 0.01667 0.00816 -0.0878 0.4062 0.5050
3.000 0.8076 0.01656 0.00833 -0.0870 0.4012 0.5939
3.250 0.8287 0.01647 0.00862 -0.0853 0.3965 0.7253
3.500 0.8585 0.01614 0.00878 -0.0847 0.3907 1.0000
3.750 0.8851 0.01638 0.00892 -0.0844 0.3857 1.0000
4.000 0.9125 0.01668 0.00907 -0.0842 0.3814 1.0000
4.250 0.9387 0.01706 0.00938 -0.0839 0.3768 1.0000
4.500 0.9635 0.01731 0.00965 -0.0833 0.3717 1.0000
4.750 0.9894 0.01757 0.00984 -0.0828 0.3670 1.0000
5.000 1.0163 0.01789 0.01004 -0.0826 0.3629 1.0000
5.250 1.0423 0.01833 0.01043 -0.0823 0.3588 1.0000
5.500 1.0661 0.01865 0.01080 -0.0816 0.3544 1.0000
5.750 1.0911 0.01895 0.01108 -0.0810 0.3501 1.0000
6.000 1.1171 0.01926 0.01130 -0.0807 0.3462 1.0000
6.250 1.1449 0.01979 0.01170 -0.0807 0.3422 1.0000
6.500 1.1662 0.02013 0.01215 -0.0796 0.3383 1.0000
6.750 1.1895 0.02050 0.01255 -0.0789 0.3343 1.0000
7.000 1.2142 0.02085 0.01288 -0.0784 0.3307 1.0000
7.250 1.2402 0.02124 0.01319 -0.0781 0.3273 1.0000
7.500 1.2664 0.02184 0.01372 -0.0779 0.3238 1.0000
7.750 1.2856 0.02225 0.01426 -0.0766 0.3201 1.0000
8.000 1.3072 0.02267 0.01472 -0.0756 0.3163 1.0000
8.250 1.3307 0.02306 0.01510 -0.0750 0.3130 1.0000
8.500 1.3561 0.02349 0.01547 -0.0747 0.3100 1.0000
8.750 1.3836 0.02421 0.01610 -0.0748 0.3068 1.0000
9.000 1.3992 0.02474 0.01679 -0.0731 0.3038 1.0000
9.250 1.4171 0.02526 0.01741 -0.0717 0.3004 1.0000
9.500 1.4374 0.02572 0.01789 -0.0707 0.2971 1.0000
9.750 1.4607 0.02615 0.01829 -0.0701 0.2942 1.0000
10.000 1.4876 0.02672 0.01878 -0.0701 0.2915 1.0000
10.250 1.5070 0.02754 0.01966 -0.0692 0.2888 1.0000
10.500 1.5179 0.02826 0.02054 -0.0670 0.2861 1.0000
10.750 1.5311 0.02893 0.02132 -0.0651 0.2831 1.0000
11.000 1.5476 0.02950 0.02193 -0.0637 0.2803 1.0000
11.250 1.5684 0.02998 0.02239 -0.0628 0.2776 1.0000
11.500 1.5960 0.03055 0.02289 -0.0631 0.2752 1.0000
11.750 1.6145 0.03155 0.02393 -0.0622 0.2727 1.0000
12.000 1.6106 0.03247 0.02504 -0.0581 0.2705 1.0000
12.250 1.6098 0.03347 0.02619 -0.0546 0.2679 1.0000
12.500 1.6148 0.03440 0.02721 -0.0522 0.2654 1.0000
12.750 1.6268 0.03517 0.02802 -0.0506 0.2630 1.0000
13.000 1.6478 0.03573 0.02856 -0.0501 0.2607 1.0000
13.250 1.6839 0.03623 0.02894 -0.0513 0.2580 1.0000
13.500 1.6760 0.03780 0.03069 -0.0480 0.2560 1.0000
13.750 1.6577 0.03983 0.03295 -0.0443 0.2538 1.0000
14.000 1.6431 0.04208 0.03538 -0.0416 0.2514 1.0000
14.250 1.6369 0.04410 0.03752 -0.0399 0.2489 1.0000
14.500 1.6464 0.04528 0.03873 -0.0391 0.2466 1.0000
14.750 1.6754 0.04532 0.03871 -0.0390 0.2443 1.0000
15.000 1.7125 0.04543 0.03871 -0.0396 0.2416 1.0000
15.250 1.6635 0.05034 0.04395 -0.0369 0.2396 1.0000
15.500 1.5883 0.05888 0.05287 -0.0362 0.2367 1.0000
15.750 1.3604 0.08984 0.08441 -0.0454 0.2279 1.0000
16.000 1.4653 0.07820 0.07263 -0.0405 0.2292 1.0000
16.250 1.5774 0.06750 0.06170 -0.0366 0.2289 1.0000
16.500 1.6642 0.06143 0.05539 -0.0351 0.2271 1.0000
16.750 0.9785 0.17752 0.17261 -0.0882 0.1751 1.0000
17.000 1.0023 0.17682 0.17192 -0.0874 0.1737 1.0000
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Polar data table (+)
Polar graphs
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