EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1211 AIRFOIL (e1211-il) Reynolds number: 100,000 Max Cl/Cd: 44.03 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1211-il-100000-n5.txt Download as CSV file: xf-e1211-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4209 0.08587 0.08029 -0.0512 1.0000 0.0872
-11.250 -0.6801 0.04571 0.03994 -0.0741 1.0000 0.0949
-11.000 -0.7329 0.03981 0.03393 -0.0755 1.0000 0.0947
-10.750 -0.7389 0.03833 0.03250 -0.0738 1.0000 0.0968
-10.500 -0.7210 0.03584 0.02982 -0.0776 0.9905 0.1021
-10.250 -0.6861 0.03489 0.02884 -0.0810 0.9758 0.1078
-10.000 -0.6586 0.03334 0.02711 -0.0839 0.9554 0.1143
-9.750 -0.6262 0.03244 0.02605 -0.0865 0.9375 0.1213
-9.500 -0.5853 0.03272 0.02640 -0.0886 0.9226 0.1269
-9.250 -0.5518 0.03104 0.02437 -0.0920 0.9056 0.1339
-9.000 -0.5090 0.03123 0.02462 -0.0941 0.8895 0.1378
-8.750 -0.4773 0.02947 0.02241 -0.0969 0.8705 0.1441
-8.500 -0.4392 0.02936 0.02229 -0.0985 0.8515 0.1476
-8.250 -0.4064 0.02894 0.02173 -0.0995 0.8319 0.1518
-8.000 -0.3820 0.02756 0.01989 -0.1003 0.8124 0.1575
-7.750 -0.3512 0.02758 0.01990 -0.1003 0.7941 0.1604
-7.500 -0.3244 0.02729 0.01948 -0.1001 0.7762 0.1642
-7.250 -0.3012 0.02634 0.01815 -0.1000 0.7595 0.1696
-7.000 -0.2745 0.02603 0.01775 -0.0997 0.7440 0.1729
-6.750 -0.2471 0.02586 0.01749 -0.0994 0.7297 0.1763
-6.500 -0.2222 0.02540 0.01686 -0.0990 0.7148 0.1807
-6.250 -0.1977 0.02467 0.01576 -0.0987 0.7016 0.1856
-6.000 -0.1710 0.02450 0.01559 -0.0982 0.6887 0.1885
-5.750 -0.1450 0.02427 0.01529 -0.0977 0.6758 0.1921
-5.500 -0.1189 0.02389 0.01467 -0.0973 0.6645 0.1965
-5.250 -0.0937 0.02337 0.01388 -0.0970 0.6521 0.2012
-5.000 -0.0670 0.02314 0.01362 -0.0965 0.6416 0.2042
-4.750 -0.0410 0.02292 0.01337 -0.0960 0.6296 0.2078
-4.500 -0.0144 0.02266 0.01292 -0.0956 0.6199 0.2121
-4.250 0.0117 0.02232 0.01238 -0.0952 0.6087 0.2167
-4.000 0.0384 0.02204 0.01197 -0.0948 0.5997 0.2202
-3.750 0.0646 0.02185 0.01180 -0.0943 0.5887 0.2238
-3.500 0.0914 0.02167 0.01149 -0.0939 0.5800 0.2280
-3.250 0.1180 0.02145 0.01116 -0.0935 0.5700 0.2326
-3.000 0.1448 0.02124 0.01076 -0.0931 0.5611 0.2369
-2.750 0.1713 0.02106 0.01060 -0.0927 0.5522 0.2406
-2.500 0.1979 0.02092 0.01043 -0.0922 0.5432 0.2448
-2.250 0.2249 0.02081 0.01018 -0.0918 0.5355 0.2496
-2.000 0.2517 0.02069 0.00996 -0.0914 0.5263 0.2546
-1.750 0.2783 0.02055 0.00977 -0.0910 0.5188 0.2587
-1.500 0.3048 0.02047 0.00970 -0.0905 0.5107 0.2633
-1.250 0.3314 0.02040 0.00959 -0.0901 0.5025 0.2687
-1.000 0.3587 0.02037 0.00938 -0.0897 0.4959 0.2744
-0.750 0.3847 0.02029 0.00938 -0.0892 0.4877 0.2793
-0.500 0.4112 0.02025 0.00933 -0.0887 0.4806 0.2848
-0.250 0.4380 0.02026 0.00925 -0.0883 0.4742 0.2916
0.000 0.4641 0.02025 0.00928 -0.0879 0.4664 0.2982
0.250 0.4903 0.02024 0.00927 -0.0874 0.4599 0.3050
0.500 0.5169 0.02029 0.00926 -0.0869 0.4539 0.3131
0.750 0.5427 0.02032 0.00936 -0.0864 0.4469 0.3213
1.000 0.5687 0.02036 0.00940 -0.0859 0.4407 0.3312
1.250 0.5951 0.02043 0.00943 -0.0854 0.4351 0.3422
1.500 0.6205 0.02051 0.00961 -0.0849 0.4284 0.3545
1.750 0.6462 0.02058 0.00972 -0.0843 0.4225 0.3688
2.000 0.6724 0.02067 0.00978 -0.0839 0.4177 0.3870
2.250 0.6971 0.02078 0.01003 -0.0832 0.4115 0.4088
2.500 0.7223 0.02087 0.01024 -0.0827 0.4056 0.4364
2.750 0.7480 0.02095 0.01038 -0.0821 0.4006 0.4730
3.000 0.7730 0.02104 0.01062 -0.0815 0.3959 0.5216
3.250 0.7960 0.02111 0.01097 -0.0805 0.3903 0.5862
3.500 0.8175 0.02109 0.01123 -0.0790 0.3853 0.6731
3.750 0.8364 0.02094 0.01138 -0.0766 0.3811 0.8027
4.000 0.8699 0.02106 0.01160 -0.0774 0.3760 1.0000
4.250 0.8940 0.02145 0.01195 -0.0769 0.3708 1.0000
4.500 0.9187 0.02179 0.01221 -0.0763 0.3662 1.0000
4.750 0.9442 0.02213 0.01241 -0.0759 0.3622 1.0000
5.000 0.9680 0.02255 0.01280 -0.0753 0.3578 1.0000
5.250 0.9907 0.02300 0.01325 -0.0745 0.3530 1.0000
5.500 1.0143 0.02341 0.01362 -0.0739 0.3487 1.0000
5.750 1.0387 0.02379 0.01392 -0.0734 0.3451 1.0000
6.000 1.0633 0.02422 0.01425 -0.0729 0.3416 1.0000
6.250 1.0833 0.02478 0.01489 -0.0718 0.3370 1.0000
6.500 1.1047 0.02527 0.01540 -0.0709 0.3327 1.0000
6.750 1.1273 0.02572 0.01580 -0.0702 0.3290 1.0000
7.000 1.1514 0.02615 0.01615 -0.0696 0.3260 1.0000
7.250 1.1724 0.02674 0.01675 -0.0688 0.3226 1.0000
7.500 1.1897 0.02741 0.01751 -0.0674 0.3186 1.0000
7.750 1.2085 0.02800 0.01813 -0.0663 0.3149 1.0000
8.000 1.2291 0.02851 0.01861 -0.0654 0.3114 1.0000
8.250 1.2520 0.02898 0.01902 -0.0647 0.3086 1.0000
8.500 1.2704 0.02966 0.01973 -0.0636 0.3056 1.0000
8.750 1.2821 0.03054 0.02074 -0.0617 0.3022 1.0000
9.000 1.2951 0.03133 0.02161 -0.0600 0.2988 1.0000
9.250 1.3097 0.03201 0.02231 -0.0584 0.2958 1.0000
9.500 1.3278 0.03258 0.02285 -0.0572 0.2930 1.0000
9.750 1.3509 0.03308 0.02327 -0.0567 0.2905 1.0000
10.000 1.3521 0.03429 0.02465 -0.0538 0.2875 1.0000
10.250 1.3529 0.03562 0.02613 -0.0511 0.2845 1.0000
10.500 1.3576 0.03689 0.02749 -0.0491 0.2816 1.0000
10.750 1.3669 0.03797 0.02862 -0.0476 0.2789 1.0000
11.000 1.3822 0.03879 0.02944 -0.0466 0.2765 1.0000
11.250 1.4049 0.03930 0.02989 -0.0462 0.2742 1.0000
11.500 1.3954 0.04152 0.03229 -0.0439 0.2715 1.0000
11.750 1.3714 0.04495 0.03597 -0.0417 0.2681 1.0000
12.000 1.3542 0.04839 0.03958 -0.0405 0.2650 1.0000
12.250 1.3507 0.05100 0.04227 -0.0399 0.2623 1.0000
12.500 1.3647 0.05215 0.04343 -0.0394 0.2601 1.0000
12.750 1.3930 0.05209 0.04331 -0.0390 0.2583 1.0000
13.250 1.1604 0.08590 0.07790 -0.0475 0.2413 1.0000
13.500 1.2078 0.08228 0.07423 -0.0454 0.2419 1.0000
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Polar data table (+)
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