EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il) Reynolds number: 200,000 Max Cl/Cd: 51.63 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1212mod-il-200000.txt Download as CSV file: xf-e1212mod-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E1212MOD 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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.5044 0.19553 0.19139 0.0122 1.0000 0.0668
-17.000 -0.4931 0.19205 0.18792 0.0113 1.0000 0.0672
-16.750 -0.7912 0.11160 0.10677 -0.0267 1.0000 0.0447
-16.500 -0.7934 0.10754 0.10269 -0.0287 1.0000 0.0453
-16.250 -0.7788 0.10664 0.10187 -0.0286 1.0000 0.0462
-16.000 -0.7814 0.10254 0.09775 -0.0307 1.0000 0.0470
-15.750 -0.7905 0.09733 0.09247 -0.0334 1.0000 0.0480
-15.500 -0.8021 0.09178 0.08682 -0.0363 1.0000 0.0489
-15.250 -0.8134 0.08646 0.08143 -0.0392 1.0000 0.0501
-15.000 -0.8086 0.08405 0.07910 -0.0401 1.0000 0.0515
-14.750 -0.8180 0.07932 0.07435 -0.0426 1.0000 0.0532
-14.500 -0.8348 0.07375 0.06869 -0.0456 1.0000 0.0546
-14.250 -0.8488 0.06892 0.06391 -0.0482 1.0000 0.0567
-14.000 -0.8698 0.06308 0.05803 -0.0515 1.0000 0.0584
-13.750 -0.8914 0.05717 0.05203 -0.0550 1.0000 0.0595
-13.500 -0.9184 0.05049 0.04525 -0.0591 1.0000 0.0612
-13.250 -0.9443 0.04382 0.03852 -0.0638 1.0000 0.0626
-13.000 -0.9653 0.03778 0.03233 -0.0685 1.0000 0.0641
-12.750 -0.9830 0.03346 0.02784 -0.0708 1.0000 0.0670
-12.500 -0.9976 0.03082 0.02517 -0.0699 1.0000 0.0693
-12.000 -1.0071 0.02776 0.02200 -0.0648 1.0000 0.0778
-11.750 -1.0004 0.02666 0.02087 -0.0629 1.0000 0.0832
-11.500 -0.9891 0.02579 0.01994 -0.0612 1.0000 0.0889
-11.250 -0.9746 0.02518 0.01929 -0.0597 1.0000 0.0944
-11.000 -0.9586 0.02470 0.01881 -0.0583 1.0000 0.0988
-10.750 -0.9418 0.02419 0.01817 -0.0568 1.0000 0.1038
-10.500 -0.9233 0.02401 0.01803 -0.0555 1.0000 0.1078
-10.250 -0.9061 0.02365 0.01754 -0.0539 1.0000 0.1127
-10.000 -0.8878 0.02350 0.01745 -0.0525 1.0000 0.1161
-9.750 -0.8708 0.02330 0.01723 -0.0508 1.0000 0.1197
-9.500 -0.8589 0.02289 0.01667 -0.0486 0.9994 0.1235
-9.250 -0.8122 0.02287 0.01676 -0.0524 0.9829 0.1281
-9.000 -0.7686 0.02247 0.01608 -0.0558 0.9645 0.1343
-8.750 -0.7235 0.02224 0.01597 -0.0590 0.9440 0.1384
-8.500 -0.6807 0.02197 0.01553 -0.0619 0.9175 0.1441
-8.250 -0.6426 0.02156 0.01499 -0.0638 0.8889 0.1488
-8.000 -0.6117 0.02155 0.01493 -0.0640 0.8608 0.1531
-7.750 -0.5877 0.02145 0.01457 -0.0630 0.8355 0.1577
-7.500 -0.5648 0.02111 0.01406 -0.0619 0.8125 0.1617
-7.250 -0.5403 0.02109 0.01402 -0.0609 0.7906 0.1656
-7.000 -0.5169 0.02106 0.01383 -0.0598 0.7695 0.1701
-6.750 -0.4943 0.02101 0.01348 -0.0585 0.7491 0.1740
-6.500 -0.4697 0.02046 0.01294 -0.0578 0.7298 0.1780
-6.250 -0.4446 0.02036 0.01278 -0.0569 0.7118 0.1820
-6.000 -0.4199 0.02025 0.01247 -0.0561 0.6958 0.1866
-5.750 -0.3953 0.01993 0.01198 -0.0553 0.6795 0.1907
-5.500 -0.3690 0.01958 0.01169 -0.0548 0.6651 0.1950
-5.250 -0.3430 0.01945 0.01145 -0.0542 0.6532 0.1993
-5.000 -0.3169 0.01927 0.01113 -0.0536 0.6406 0.2038
-4.750 -0.2911 0.01887 0.01058 -0.0530 0.6305 0.2079
-4.500 -0.2642 0.01860 0.01036 -0.0526 0.6196 0.2119
-4.250 -0.2374 0.01841 0.01005 -0.0521 0.6107 0.2155
-4.000 -0.2104 0.01812 0.00967 -0.0516 0.6010 0.2187
-3.750 -0.1835 0.01790 0.00924 -0.0511 0.5926 0.2216
-3.500 -0.1564 0.01749 0.00879 -0.0507 0.5839 0.2247
-3.250 -0.1291 0.01722 0.00850 -0.0503 0.5754 0.2277
-3.000 -0.1018 0.01707 0.00828 -0.0499 0.5677 0.2309
-2.750 -0.0744 0.01689 0.00807 -0.0495 0.5589 0.2348
-2.500 -0.0470 0.01680 0.00781 -0.0490 0.5511 0.2387
-2.250 -0.0197 0.01656 0.00757 -0.0487 0.5432 0.2426
-2.000 0.0075 0.01642 0.00744 -0.0482 0.5348 0.2467
-1.750 0.0350 0.01643 0.00733 -0.0478 0.5273 0.2517
-1.500 0.0625 0.01634 0.00721 -0.0474 0.5193 0.2574
-1.250 0.0894 0.01618 0.00711 -0.0469 0.5116 0.2635
-1.000 0.1169 0.01626 0.00710 -0.0465 0.5045 0.2711
-0.750 0.1439 0.01611 0.00701 -0.0460 0.4965 0.2792
-0.500 0.1710 0.01606 0.00695 -0.0455 0.4889 0.2890
-0.250 0.1980 0.01604 0.00691 -0.0451 0.4818 0.3008
0.000 0.2249 0.01599 0.00687 -0.0446 0.4736 0.3151
0.250 0.2514 0.01585 0.00680 -0.0440 0.4665 0.3304
0.500 0.2781 0.01585 0.00681 -0.0435 0.4598 0.3462
0.750 0.3046 0.01576 0.00681 -0.0430 0.4520 0.3620
1.000 0.3316 0.01575 0.00677 -0.0425 0.4452 0.3775
1.250 0.3583 0.01577 0.00683 -0.0420 0.4387 0.3919
1.500 0.3848 0.01571 0.00686 -0.0414 0.4310 0.4066
1.750 0.4118 0.01569 0.00681 -0.0409 0.4245 0.4226
2.000 0.4382 0.01569 0.00686 -0.0404 0.4181 0.4393
2.250 0.4643 0.01560 0.00689 -0.0398 0.4107 0.4574
2.500 0.4904 0.01550 0.00684 -0.0392 0.4047 0.4795
2.750 0.5159 0.01547 0.00692 -0.0385 0.3989 0.5098
3.000 0.5396 0.01529 0.00706 -0.0374 0.3925 0.5661
3.250 0.5599 0.01491 0.00718 -0.0355 0.3873 0.7010
3.500 0.6255 0.01472 0.00746 -0.0417 0.3799 0.9428
3.750 0.6909 0.01494 0.00763 -0.0489 0.3720 1.0000
4.000 0.7143 0.01516 0.00773 -0.0479 0.3675 1.0000
4.250 0.7382 0.01553 0.00794 -0.0471 0.3632 1.0000
4.500 0.7610 0.01578 0.00822 -0.0460 0.3587 1.0000
4.750 0.7843 0.01605 0.00845 -0.0450 0.3541 1.0000
5.000 0.8082 0.01632 0.00864 -0.0440 0.3501 1.0000
5.250 0.8329 0.01670 0.00888 -0.0433 0.3464 1.0000
5.500 0.8562 0.01710 0.00928 -0.0423 0.3429 1.0000
5.750 0.8793 0.01744 0.00966 -0.0413 0.3394 1.0000
6.000 0.9030 0.01779 0.01001 -0.0404 0.3361 1.0000
6.250 0.9273 0.01814 0.01032 -0.0397 0.3330 1.0000
6.500 0.9522 0.01853 0.01065 -0.0390 0.3303 1.0000
6.750 0.9780 0.01907 0.01110 -0.0385 0.3277 1.0000
7.000 1.0014 0.01961 0.01167 -0.0377 0.3253 1.0000
7.250 1.0238 0.02006 0.01222 -0.0367 0.3230 1.0000
7.500 1.0466 0.02054 0.01275 -0.0358 0.3205 1.0000
7.750 1.0698 0.02099 0.01323 -0.0350 0.3178 1.0000
8.000 1.0939 0.02134 0.01357 -0.0342 0.3149 1.0000
8.250 1.1193 0.02168 0.01384 -0.0337 0.3120 1.0000
8.500 1.1457 0.02234 0.01440 -0.0335 0.3089 1.0000
8.750 1.1661 0.02285 0.01503 -0.0323 0.3067 1.0000
9.000 1.1860 0.02337 0.01567 -0.0311 0.3043 1.0000
9.250 1.2066 0.02387 0.01625 -0.0300 0.3016 1.0000
9.500 1.2284 0.02434 0.01676 -0.0291 0.2990 1.0000
9.750 1.2515 0.02477 0.01720 -0.0283 0.2967 1.0000
10.000 1.2766 0.02517 0.01756 -0.0278 0.2943 1.0000
10.250 1.3038 0.02578 0.01807 -0.0277 0.2915 1.0000
10.500 1.3201 0.02640 0.01884 -0.0262 0.2890 1.0000
10.750 1.3354 0.02702 0.01960 -0.0245 0.2865 1.0000
11.000 1.3516 0.02762 0.02032 -0.0230 0.2838 1.0000
11.250 1.3702 0.02814 0.02089 -0.0218 0.2813 1.0000
11.500 1.3917 0.02853 0.02130 -0.0209 0.2788 1.0000
11.750 1.4177 0.02884 0.02154 -0.0206 0.2763 1.0000
12.000 1.4448 0.02959 0.02223 -0.0206 0.2736 1.0000
12.250 1.4509 0.03035 0.02320 -0.0179 0.2715 1.0000
12.500 1.4561 0.03119 0.02421 -0.0153 0.2689 1.0000
12.750 1.4632 0.03193 0.02506 -0.0129 0.2661 1.0000
13.000 1.4749 0.03238 0.02557 -0.0108 0.2633 1.0000
13.250 1.4975 0.03253 0.02567 -0.0100 0.2605 1.0000
13.500 1.5359 0.03282 0.02581 -0.0113 0.2570 1.0000
13.750 1.5179 0.03395 0.02717 -0.0060 0.2549 1.0000
14.000 1.5018 0.03542 0.02883 -0.0021 0.2521 1.0000
14.250 1.4961 0.03678 0.03032 0.0003 0.2490 1.0000
14.500 1.5085 0.03731 0.03085 0.0015 0.2458 1.0000
14.750 1.5462 0.03669 0.03008 0.0014 0.2421 1.0000
15.000 1.5302 0.03892 0.03249 0.0035 0.2390 1.0000
15.250 1.4994 0.04244 0.03624 0.0051 0.2355 1.0000
15.500 1.4952 0.04435 0.03823 0.0058 0.2313 1.0000
15.750 1.5253 0.04368 0.03744 0.0064 0.2274 1.0000
16.000 1.5112 0.04670 0.04058 0.0068 0.2232 1.0000
16.250 1.4671 0.05285 0.04698 0.0058 0.2183 1.0000
16.500 1.4832 0.05330 0.04738 0.0062 0.2136 1.0000
16.750 1.4912 0.05473 0.04879 0.0063 0.2090 1.0000
17.000 1.4233 0.06491 0.05927 0.0027 0.2024 1.0000
17.250 1.4502 0.06421 0.05847 0.0035 0.1982 1.0000
17.500 1.3946 0.07408 0.06855 -0.0004 0.1916 1.0000
17.750 1.3832 0.07853 0.07304 -0.0020 0.1863 1.0000
18.000 1.4331 0.07464 0.06897 0.0003 0.1831 1.0000
18.250 1.2933 0.09785 0.09260 -0.0104 0.1737 1.0000
18.500 1.3508 0.09234 0.08697 -0.0073 0.1720 1.0000
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