EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 1211 AIRFOIL (e1211-il) Reynolds number: 500,000 Max Cl/Cd: 88.97 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1211-il-500000.txt Download as CSV file: xf-e1211-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7277 0.08972 0.08575 -0.0531 1.0000 0.0298
-15.750 -0.7294 0.08626 0.08226 -0.0547 1.0000 0.0302
-15.500 -0.7316 0.08275 0.07874 -0.0563 1.0000 0.0307
-15.250 -0.7354 0.07907 0.07503 -0.0580 1.0000 0.0313
-15.000 -0.7410 0.07520 0.07113 -0.0598 1.0000 0.0316
-14.750 -0.7480 0.07126 0.06714 -0.0617 1.0000 0.0321
-14.500 -0.7615 0.06676 0.06261 -0.0639 1.0000 0.0324
-14.250 -0.7824 0.06158 0.05741 -0.0666 1.0000 0.0328
-14.000 -0.8090 0.05585 0.05162 -0.0695 1.0000 0.0329
-13.750 -0.8466 0.04906 0.04472 -0.0729 1.0000 0.0328
-13.500 -0.8891 0.04192 0.03746 -0.0761 1.0000 0.0324
-13.250 -0.9720 0.02982 0.02503 -0.0837 1.0000 0.0314
-13.000 -0.9807 0.02725 0.02233 -0.0828 1.0000 0.0318
-12.750 -0.9807 0.02551 0.02050 -0.0813 1.0000 0.0324
-12.500 -0.9785 0.02391 0.01884 -0.0796 1.0000 0.0333
-12.250 -0.9597 0.02253 0.01740 -0.0801 0.9986 0.0348
-12.000 -0.9226 0.02107 0.01589 -0.0837 0.9943 0.0373
-11.750 -0.8865 0.01970 0.01447 -0.0868 0.9897 0.0413
-11.500 -0.8520 0.01835 0.01312 -0.0895 0.9834 0.0483
-11.250 -0.8164 0.01715 0.01194 -0.0920 0.9772 0.0585
-11.000 -0.7839 0.01628 0.01108 -0.0935 0.9666 0.0674
-10.750 -0.7534 0.01557 0.01038 -0.0942 0.9515 0.0748
-10.500 -0.7159 0.01495 0.00975 -0.0962 0.9375 0.0820
-10.250 -0.6667 0.01438 0.00915 -0.1005 0.9241 0.0893
-10.000 -0.6141 0.01387 0.00858 -0.1053 0.9034 0.0966
-9.750 -0.5745 0.01358 0.00815 -0.1074 0.8706 0.1027
-9.250 -0.5204 0.01328 0.00755 -0.1066 0.8126 0.1123
-9.000 -0.4953 0.01310 0.00729 -0.1059 0.7897 0.1166
-8.750 -0.4693 0.01301 0.00707 -0.1053 0.7694 0.1211
-8.500 -0.4437 0.01287 0.00684 -0.1046 0.7507 0.1252
-8.250 -0.4172 0.01278 0.00668 -0.1041 0.7333 0.1297
-8.000 -0.3902 0.01271 0.00650 -0.1036 0.7175 0.1341
-7.750 -0.3638 0.01262 0.00637 -0.1030 0.7025 0.1385
-7.500 -0.3366 0.01262 0.00625 -0.1026 0.6878 0.1428
-7.250 -0.3094 0.01250 0.00607 -0.1021 0.6745 0.1468
-7.000 -0.2823 0.01246 0.00598 -0.1017 0.6614 0.1507
-6.750 -0.2546 0.01246 0.00589 -0.1013 0.6485 0.1546
-6.500 -0.2270 0.01241 0.00574 -0.1009 0.6369 0.1583
-6.250 -0.1998 0.01232 0.00564 -0.1005 0.6249 0.1622
-6.000 -0.1719 0.01232 0.00558 -0.1002 0.6138 0.1659
-5.750 -0.1441 0.01235 0.00549 -0.0998 0.6025 0.1693
-5.500 -0.1164 0.01219 0.00528 -0.0995 0.5924 0.1726
-5.250 -0.0890 0.01211 0.00517 -0.0991 0.5817 0.1759
-5.000 -0.0609 0.01208 0.00511 -0.0988 0.5719 0.1792
-4.750 -0.0330 0.01208 0.00502 -0.0984 0.5620 0.1824
-4.500 -0.0047 0.01210 0.00494 -0.0982 0.5530 0.1849
-4.250 0.0226 0.01187 0.00470 -0.0978 0.5434 0.1887
-4.000 0.0504 0.01183 0.00463 -0.0975 0.5345 0.1919
-3.750 0.0787 0.01180 0.00457 -0.0972 0.5256 0.1951
-3.500 0.1064 0.01182 0.00449 -0.0969 0.5171 0.1982
-3.250 0.1351 0.01182 0.00444 -0.0966 0.5091 0.2006
-3.000 0.1624 0.01164 0.00423 -0.0963 0.5005 0.2044
-2.750 0.1902 0.01159 0.00417 -0.0960 0.4927 0.2078
-2.500 0.2184 0.01157 0.00413 -0.0957 0.4846 0.2112
-2.250 0.2461 0.01160 0.00408 -0.0954 0.4770 0.2144
-2.000 0.2747 0.01160 0.00405 -0.0952 0.4699 0.2172
-1.750 0.3023 0.01150 0.00392 -0.0949 0.4622 0.2210
-1.500 0.3297 0.01147 0.00387 -0.0945 0.4549 0.2248
-1.250 0.3580 0.01145 0.00385 -0.0943 0.4479 0.2286
-1.000 0.3858 0.01149 0.00384 -0.0940 0.4410 0.2324
-0.750 0.4137 0.01155 0.00384 -0.0937 0.4344 0.2355
-0.500 0.4416 0.01146 0.00377 -0.0935 0.4278 0.2400
-0.250 0.4689 0.01147 0.00376 -0.0931 0.4209 0.2449
0.000 0.4966 0.01151 0.00379 -0.0928 0.4148 0.2495
0.250 0.5248 0.01154 0.00380 -0.0926 0.4088 0.2538
0.500 0.5521 0.01155 0.00379 -0.0923 0.4026 0.2590
0.750 0.5792 0.01160 0.00384 -0.0919 0.3966 0.2654
1.000 0.6073 0.01161 0.00387 -0.0917 0.3910 0.2717
1.250 0.6347 0.01167 0.00390 -0.0914 0.3852 0.2781
1.500 0.6612 0.01176 0.00398 -0.0909 0.3794 0.2866
1.750 0.6893 0.01178 0.00404 -0.0907 0.3748 0.2954
2.000 0.7166 0.01179 0.00410 -0.0904 0.3693 0.3078
2.250 0.7433 0.01188 0.00418 -0.0900 0.3639 0.3214
2.500 0.7700 0.01196 0.00430 -0.0897 0.3591 0.3389
2.750 0.7975 0.01195 0.00440 -0.0894 0.3548 0.3631
3.000 0.8243 0.01197 0.00452 -0.0891 0.3500 0.3961
3.250 0.8502 0.01203 0.00466 -0.0887 0.3451 0.4397
3.500 0.8764 0.01206 0.00484 -0.0883 0.3407 0.4949
3.750 0.9029 0.01199 0.00500 -0.0879 0.3366 0.5642
4.000 0.9281 0.01193 0.00518 -0.0873 0.3325 0.6492
4.250 0.9506 0.01185 0.00539 -0.0860 0.3284 0.7587
4.500 0.9767 0.01169 0.00559 -0.0851 0.3240 1.0000
4.750 1.0036 0.01182 0.00573 -0.0848 0.3206 1.0000
5.000 1.0299 0.01198 0.00587 -0.0844 0.3166 1.0000
5.250 1.0553 0.01219 0.00603 -0.0839 0.3127 1.0000
5.500 1.0798 0.01249 0.00625 -0.0832 0.3086 1.0000
5.750 1.1053 0.01271 0.00646 -0.0827 0.3054 1.0000
6.000 1.1311 0.01288 0.00664 -0.0822 0.3022 1.0000
6.250 1.1562 0.01308 0.00683 -0.0816 0.2987 1.0000
6.500 1.1804 0.01333 0.00703 -0.0809 0.2952 1.0000
6.750 1.2034 0.01367 0.00731 -0.0801 0.2912 1.0000
7.000 1.2277 0.01391 0.00756 -0.0794 0.2883 1.0000
7.250 1.2521 0.01411 0.00778 -0.0788 0.2855 1.0000
7.500 1.2758 0.01434 0.00802 -0.0780 0.2824 1.0000
7.750 1.2985 0.01461 0.00827 -0.0771 0.2794 1.0000
8.000 1.3199 0.01495 0.00857 -0.0760 0.2762 1.0000
8.250 1.3412 0.01534 0.00894 -0.0750 0.2729 1.0000
8.500 1.3632 0.01556 0.00920 -0.0740 0.2705 1.0000
8.750 1.3834 0.01580 0.00947 -0.0726 0.2676 1.0000
9.000 1.4026 0.01608 0.00977 -0.0712 0.2649 1.0000
9.250 1.4204 0.01643 0.01010 -0.0695 0.2623 1.0000
9.500 1.4373 0.01687 0.01051 -0.0678 0.2594 1.0000
9.750 1.4551 0.01732 0.01096 -0.0664 0.2568 1.0000
10.000 1.4733 0.01764 0.01134 -0.0649 0.2547 1.0000
10.250 1.4909 0.01798 0.01173 -0.0634 0.2523 1.0000
10.500 1.5078 0.01838 0.01215 -0.0619 0.2498 1.0000
10.750 1.5234 0.01883 0.01262 -0.0602 0.2472 1.0000
11.000 1.5380 0.01939 0.01316 -0.0586 0.2448 1.0000
11.250 1.5530 0.02009 0.01382 -0.0570 0.2418 1.0000
11.500 1.5679 0.02057 0.01440 -0.0555 0.2402 1.0000
11.750 1.5823 0.02113 0.01502 -0.0540 0.2381 1.0000
12.000 1.5960 0.02174 0.01569 -0.0526 0.2358 1.0000
12.250 1.6091 0.02243 0.01641 -0.0512 0.2336 1.0000
12.500 1.6212 0.02321 0.01721 -0.0497 0.2314 1.0000
12.750 1.6323 0.02411 0.01810 -0.0483 0.2290 1.0000
13.000 1.6446 0.02504 0.01903 -0.0471 0.2263 1.0000
13.250 1.6554 0.02596 0.02005 -0.0459 0.2246 1.0000
13.500 1.6658 0.02697 0.02113 -0.0447 0.2225 1.0000
13.750 1.6758 0.02805 0.02228 -0.0437 0.2202 1.0000
14.000 1.6850 0.02922 0.02350 -0.0427 0.2180 1.0000
14.250 1.6933 0.03051 0.02480 -0.0418 0.2157 1.0000
14.500 1.7021 0.03182 0.02609 -0.0408 0.2130 1.0000
14.750 1.7105 0.03321 0.02754 -0.0400 0.2112 1.0000
15.000 1.7167 0.03478 0.02923 -0.0394 0.2092 1.0000
15.250 1.7233 0.03638 0.03091 -0.0388 0.2072 1.0000
15.500 1.7290 0.03810 0.03269 -0.0383 0.2050 1.0000
15.750 1.7340 0.03991 0.03455 -0.0379 0.2029 1.0000
16.000 1.7390 0.04174 0.03638 -0.0374 0.2006 1.0000
16.250 1.7467 0.04334 0.03797 -0.0369 0.1980 1.0000
16.500 1.7479 0.04570 0.04046 -0.0368 0.1963 1.0000
16.750 1.7492 0.04811 0.04298 -0.0368 0.1942 1.0000
17.000 1.7508 0.05055 0.04551 -0.0369 0.1919 1.0000
17.250 1.7517 0.05311 0.04813 -0.0371 0.1897 1.0000
17.500 1.7538 0.05555 0.05057 -0.0372 0.1872 1.0000
17.750 1.7594 0.05753 0.05253 -0.0372 0.1845 1.0000
18.000 1.7541 0.06107 0.05623 -0.0379 0.1826 1.0000
18.250 1.7507 0.06443 0.05971 -0.0386 0.1802 1.0000
18.500 1.7474 0.06783 0.06319 -0.0395 0.1776 1.0000
18.750 1.7448 0.07114 0.06652 -0.0403 0.1750 1.0000
19.000 1.7495 0.07338 0.06872 -0.0406 0.1720 1.0000
19.250 1.7377 0.07816 0.07367 -0.0422 0.1696 1.0000
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