EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1211 AIRFOIL (e1211-il) Reynolds number: 500,000 Max Cl/Cd: 89.58 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1211-il-500000-n5.txt Download as CSV file: xf-e1211-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6867 0.09021 0.08622 -0.0512 1.0000 0.0231
-15.250 -0.6969 0.08540 0.08137 -0.0536 1.0000 0.0234
-15.000 -0.7055 0.08092 0.07685 -0.0558 1.0000 0.0236
-14.750 -0.7200 0.07573 0.07160 -0.0585 1.0000 0.0239
-14.500 -0.7374 0.07037 0.06618 -0.0613 1.0000 0.0241
-14.250 -0.7622 0.06445 0.06019 -0.0644 1.0000 0.0242
-14.000 -0.7959 0.05771 0.05335 -0.0680 1.0000 0.0241
-13.750 -0.8471 0.04925 0.04477 -0.0724 1.0000 0.0238
-13.500 -0.9226 0.03819 0.03349 -0.0780 1.0000 0.0231
-13.250 -0.9826 0.02832 0.02324 -0.0849 0.9993 0.0227
-13.000 -0.9569 0.02582 0.02062 -0.0894 0.9939 0.0235
-12.750 -0.9320 0.02417 0.01888 -0.0917 0.9876 0.0242
-12.250 -0.8892 0.02163 0.01619 -0.0930 0.9611 0.0261
-12.000 -0.8584 0.02049 0.01498 -0.0949 0.9410 0.0277
-11.750 -0.8065 0.01918 0.01359 -0.1009 0.9240 0.0309
-11.500 -0.7495 0.01793 0.01225 -0.1078 0.8956 0.0363
-11.250 -0.7175 0.01716 0.01130 -0.1093 0.8525 0.0417
-11.000 -0.6957 0.01663 0.01062 -0.1086 0.8191 0.0465
-10.750 -0.6744 0.01615 0.01002 -0.1076 0.7928 0.0513
-10.500 -0.6524 0.01570 0.00947 -0.1068 0.7704 0.0565
-10.250 -0.6295 0.01530 0.00897 -0.1060 0.7506 0.0615
-10.000 -0.6059 0.01491 0.00851 -0.1053 0.7323 0.0669
-9.750 -0.5817 0.01456 0.00809 -0.1046 0.7157 0.0723
-9.500 -0.5570 0.01422 0.00768 -0.1040 0.7007 0.0778
-9.250 -0.5321 0.01393 0.00732 -0.1035 0.6857 0.0830
-9.000 -0.5062 0.01367 0.00700 -0.1030 0.6717 0.0879
-8.750 -0.4803 0.01342 0.00669 -0.1025 0.6589 0.0929
-8.500 -0.4541 0.01320 0.00641 -0.1020 0.6456 0.0975
-8.250 -0.4274 0.01300 0.00615 -0.1016 0.6337 0.1030
-7.750 -0.3737 0.01264 0.00569 -0.1008 0.6105 0.1138
-7.500 -0.3469 0.01249 0.00549 -0.1004 0.5992 0.1191
-7.250 -0.3192 0.01235 0.00530 -0.1001 0.5888 0.1236
-7.000 -0.2921 0.01224 0.00514 -0.0997 0.5783 0.1284
-6.750 -0.2641 0.01213 0.00498 -0.0994 0.5681 0.1327
-6.250 -0.2086 0.01194 0.00471 -0.0988 0.5492 0.1416
-6.000 -0.1809 0.01189 0.00457 -0.0985 0.5392 0.1452
-5.750 -0.1529 0.01179 0.00445 -0.0982 0.5305 0.1490
-5.500 -0.1249 0.01173 0.00434 -0.0979 0.5215 0.1524
-5.250 -0.0969 0.01169 0.00423 -0.0976 0.5131 0.1557
-5.000 -0.0687 0.01162 0.00411 -0.0973 0.5041 0.1586
-4.750 -0.0410 0.01157 0.00402 -0.0970 0.4959 0.1617
-4.500 -0.0126 0.01151 0.00393 -0.0968 0.4885 0.1649
-4.250 0.0155 0.01148 0.00384 -0.0965 0.4802 0.1680
-4.000 0.0438 0.01147 0.00376 -0.0962 0.4725 0.1704
-3.750 0.0719 0.01140 0.00367 -0.0960 0.4647 0.1734
-3.500 0.0998 0.01138 0.00361 -0.0957 0.4575 0.1765
-3.250 0.1282 0.01135 0.00356 -0.0955 0.4512 0.1794
-3.000 0.1565 0.01134 0.00350 -0.0952 0.4435 0.1823
-2.750 0.1844 0.01137 0.00345 -0.0949 0.4362 0.1848
-2.500 0.2127 0.01131 0.00339 -0.0947 0.4297 0.1876
-2.250 0.2408 0.01129 0.00336 -0.0945 0.4231 0.1908
-2.000 0.2686 0.01132 0.00334 -0.0942 0.4168 0.1940
-1.750 0.2971 0.01131 0.00331 -0.0940 0.4108 0.1970
-1.500 0.3252 0.01134 0.00329 -0.0937 0.4038 0.1997
-1.250 0.3529 0.01137 0.00328 -0.0934 0.3976 0.2026
-1.000 0.3811 0.01135 0.00327 -0.0932 0.3923 0.2061
-0.750 0.4091 0.01136 0.00327 -0.0929 0.3864 0.2094
-0.500 0.4367 0.01142 0.00329 -0.0926 0.3803 0.2131
-0.250 0.4649 0.01145 0.00330 -0.0924 0.3750 0.2164
0.000 0.4928 0.01149 0.00332 -0.0921 0.3692 0.2196
0.250 0.5203 0.01153 0.00335 -0.0918 0.3639 0.2237
0.500 0.5480 0.01158 0.00339 -0.0915 0.3591 0.2282
0.750 0.5759 0.01162 0.00343 -0.0913 0.3541 0.2327
1.250 0.6306 0.01176 0.00354 -0.0906 0.3435 0.2418
1.500 0.6583 0.01181 0.00361 -0.0904 0.3396 0.2476
1.750 0.6859 0.01187 0.00367 -0.0901 0.3350 0.2536
2.000 0.7131 0.01195 0.00376 -0.0898 0.3300 0.2606
2.250 0.7397 0.01205 0.00385 -0.0894 0.3252 0.2685
2.750 0.7944 0.01218 0.00404 -0.0888 0.3176 0.2866
3.000 0.8213 0.01227 0.00415 -0.0885 0.3135 0.2981
3.250 0.8475 0.01238 0.00428 -0.0880 0.3092 0.3135
3.500 0.8741 0.01247 0.00442 -0.0877 0.3055 0.3304
3.750 0.9010 0.01253 0.00454 -0.0873 0.3017 0.3496
4.000 0.9274 0.01262 0.00469 -0.0869 0.2980 0.3725
4.250 0.9533 0.01271 0.00485 -0.0865 0.2944 0.4010
4.500 0.9786 0.01282 0.00504 -0.0860 0.2907 0.4378
4.750 1.0048 0.01286 0.00522 -0.0856 0.2878 0.4815
5.000 1.0306 0.01290 0.00540 -0.0851 0.2842 0.5313
5.250 1.0557 0.01296 0.00560 -0.0846 0.2806 0.5893
5.500 1.0797 0.01300 0.00583 -0.0838 0.2772 0.6623
5.750 1.1012 0.01299 0.00609 -0.0825 0.2741 0.7633
6.000 1.1264 0.01278 0.00627 -0.0816 0.2716 1.0000
6.250 1.1517 0.01297 0.00646 -0.0810 0.2688 1.0000
6.500 1.1762 0.01319 0.00667 -0.0804 0.2657 1.0000
6.750 1.2000 0.01344 0.00689 -0.0797 0.2624 1.0000
7.000 1.2228 0.01372 0.00713 -0.0788 0.2591 1.0000
7.250 1.2460 0.01397 0.00738 -0.0779 0.2565 1.0000
7.500 1.2698 0.01419 0.00761 -0.0772 0.2541 1.0000
7.750 1.2927 0.01443 0.00786 -0.0763 0.2516 1.0000
8.000 1.3147 0.01470 0.00813 -0.0753 0.2488 1.0000
8.250 1.3347 0.01498 0.00840 -0.0740 0.2462 1.0000
8.500 1.3528 0.01531 0.00871 -0.0723 0.2434 1.0000
8.750 1.3713 0.01563 0.00903 -0.0707 0.2409 1.0000
9.000 1.3912 0.01590 0.00933 -0.0694 0.2387 1.0000
9.250 1.4102 0.01621 0.00967 -0.0680 0.2363 1.0000
9.500 1.4282 0.01656 0.01003 -0.0665 0.2339 1.0000
9.750 1.4453 0.01695 0.01043 -0.0649 0.2316 1.0000
10.000 1.4610 0.01740 0.01088 -0.0632 0.2293 1.0000
10.250 1.4754 0.01791 0.01139 -0.0614 0.2269 1.0000
10.500 1.4929 0.01832 0.01184 -0.0600 0.2252 1.0000
10.750 1.5095 0.01877 0.01234 -0.0586 0.2230 1.0000
11.000 1.5249 0.01929 0.01289 -0.0571 0.2206 1.0000
11.250 1.5390 0.01989 0.01352 -0.0556 0.2184 1.0000
11.500 1.5517 0.02057 0.01423 -0.0540 0.2163 1.0000
11.750 1.5629 0.02137 0.01504 -0.0523 0.2142 1.0000
12.000 1.5730 0.02228 0.01597 -0.0508 0.2120 1.0000
12.250 1.5872 0.02301 0.01676 -0.0496 0.2103 1.0000
12.500 1.6000 0.02386 0.01767 -0.0485 0.2083 1.0000
12.750 1.6116 0.02482 0.01868 -0.0473 0.2062 1.0000
13.000 1.6215 0.02592 0.01982 -0.0462 0.2040 1.0000
13.250 1.6296 0.02720 0.02113 -0.0451 0.2017 1.0000
13.500 1.6359 0.02866 0.02261 -0.0440 0.1994 1.0000
13.750 1.6439 0.03007 0.02407 -0.0431 0.1974 1.0000
14.000 1.6539 0.03136 0.02543 -0.0424 0.1955 1.0000
14.250 1.6622 0.03284 0.02698 -0.0418 0.1933 1.0000
14.500 1.6683 0.03452 0.02871 -0.0411 0.1909 1.0000
14.750 1.6727 0.03640 0.03064 -0.0406 0.1887 1.0000
15.000 1.6745 0.03856 0.03283 -0.0400 0.1864 1.0000
15.250 1.6766 0.04075 0.03506 -0.0396 0.1844 1.0000
15.500 1.6827 0.04263 0.03703 -0.0394 0.1826 1.0000
15.750 1.6870 0.04472 0.03920 -0.0392 0.1805 1.0000
16.000 1.6897 0.04703 0.04158 -0.0391 0.1783 1.0000
16.250 1.6896 0.04968 0.04429 -0.0391 0.1760 1.0000
16.500 1.6873 0.05263 0.04728 -0.0392 0.1738 1.0000
16.750 1.6846 0.05569 0.05038 -0.0395 0.1716 1.0000
17.000 1.6878 0.05818 0.05296 -0.0398 0.1697 1.0000
17.250 1.6877 0.06110 0.05598 -0.0402 0.1674 1.0000
17.500 1.6859 0.06427 0.05922 -0.0407 0.1649 1.0000
17.750 1.6818 0.06777 0.06277 -0.0415 0.1625 1.0000
18.000 1.6742 0.07178 0.06682 -0.0424 0.1600 1.0000
18.250 1.6726 0.07511 0.07024 -0.0432 0.1577 1.0000
18.500 1.6697 0.07867 0.07389 -0.0442 0.1551 1.0000
18.750 1.6631 0.08278 0.07807 -0.0454 0.1523 1.0000
19.000 1.6545 0.08720 0.08254 -0.0468 0.1494 1.0000
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Polar data table (+)
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