EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E1212 AIRFOIL (e1212-il) Reynolds number: 200,000 Max Cl/Cd: 55.25 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1212-il-200000.txt Download as CSV file: xf-e1212-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E1212 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 -0.7844 0.10749 0.10264 -0.0357 1.0000 0.0455
-17.000 -0.8129 0.09873 0.09366 -0.0409 1.0000 0.0462
-16.750 -0.8356 0.09123 0.08596 -0.0454 1.0000 0.0469
-16.500 -0.8132 0.09189 0.08683 -0.0440 1.0000 0.0487
-16.250 -0.8197 0.08739 0.08229 -0.0463 1.0000 0.0501
-16.000 -0.8358 0.08139 0.07614 -0.0498 1.0000 0.0514
-15.750 -0.8389 0.07779 0.07256 -0.0515 1.0000 0.0532
-15.500 -0.8401 0.07454 0.06933 -0.0530 1.0000 0.0549
-15.250 -0.8563 0.06913 0.06381 -0.0561 1.0000 0.0567
-15.000 -0.8645 0.06517 0.05984 -0.0580 1.0000 0.0586
-14.750 -0.8713 0.06142 0.05611 -0.0599 1.0000 0.0606
-14.500 -0.8874 0.05630 0.05089 -0.0628 1.0000 0.0626
-14.250 -0.8987 0.05204 0.04663 -0.0650 1.0000 0.0647
-14.000 -0.9106 0.04764 0.04222 -0.0675 1.0000 0.0669
-13.750 -0.9264 0.04263 0.03706 -0.0708 1.0000 0.0694
-13.500 -0.9373 0.03858 0.03301 -0.0731 1.0000 0.0717
-13.250 -0.9487 0.03477 0.02913 -0.0754 1.0000 0.0745
-13.000 -0.9608 0.03178 0.02600 -0.0759 1.0000 0.0775
-12.750 -0.9712 0.02993 0.02417 -0.0739 1.0000 0.0803
-12.500 -0.9770 0.02848 0.02258 -0.0711 1.0000 0.0846
-12.250 -0.9748 0.02731 0.02148 -0.0689 1.0000 0.0888
-12.000 -0.9687 0.02624 0.02034 -0.0668 1.0000 0.0943
-11.750 -0.9588 0.02539 0.01943 -0.0649 1.0000 0.1002
-11.500 -0.9468 0.02468 0.01875 -0.0631 1.0000 0.1056
-11.250 -0.9335 0.02398 0.01794 -0.0614 1.0000 0.1118
-11.000 -0.9180 0.02354 0.01755 -0.0598 1.0000 0.1173
-10.750 -0.9028 0.02302 0.01697 -0.0581 1.0000 0.1230
-10.500 -0.8861 0.02276 0.01673 -0.0564 1.0000 0.1285
-10.250 -0.8711 0.02236 0.01629 -0.0546 1.0000 0.1338
-10.000 -0.8561 0.02231 0.01630 -0.0526 1.0000 0.1387
-9.750 -0.8440 0.02203 0.01587 -0.0506 0.9992 0.1441
-9.500 -0.7940 0.02221 0.01620 -0.0548 0.9909 0.1513
-9.250 -0.7472 0.02195 0.01586 -0.0586 0.9803 0.1586
-9.000 -0.7019 0.02205 0.01600 -0.0617 0.9667 0.1652
-8.750 -0.6594 0.02164 0.01548 -0.0646 0.9511 0.1716
-8.500 -0.6138 0.02170 0.01562 -0.0675 0.9342 0.1773
-8.250 -0.5713 0.02122 0.01484 -0.0703 0.9137 0.1840
-8.000 -0.5287 0.02106 0.01479 -0.0726 0.8897 0.1886
-7.750 -0.4947 0.02095 0.01453 -0.0734 0.8632 0.1938
-7.500 -0.4690 0.02070 0.01392 -0.0728 0.8377 0.1988
-7.250 -0.4427 0.02038 0.01362 -0.0721 0.8146 0.2025
-7.000 -0.4169 0.02035 0.01351 -0.0713 0.7940 0.2065
-6.750 -0.3923 0.02020 0.01314 -0.0704 0.7752 0.2113
-6.500 -0.3681 0.01987 0.01254 -0.0695 0.7578 0.2157
-6.250 -0.3421 0.01955 0.01225 -0.0689 0.7407 0.2193
-6.000 -0.3160 0.01944 0.01208 -0.0682 0.7248 0.2234
-5.750 -0.2903 0.01927 0.01172 -0.0675 0.7105 0.2280
-5.500 -0.2648 0.01911 0.01129 -0.0668 0.6963 0.2322
-5.250 -0.2385 0.01860 0.01082 -0.0664 0.6823 0.2362
-5.000 -0.2119 0.01847 0.01061 -0.0658 0.6699 0.2402
-4.750 -0.1854 0.01830 0.01033 -0.0653 0.6567 0.2448
-4.500 -0.1587 0.01817 0.01001 -0.0647 0.6446 0.2491
-4.250 -0.1323 0.01773 0.00949 -0.0643 0.6331 0.2531
-4.000 -0.1052 0.01754 0.00931 -0.0639 0.6212 0.2572
-3.750 -0.0781 0.01743 0.00908 -0.0634 0.6107 0.2617
-3.500 -0.0510 0.01728 0.00882 -0.0630 0.5990 0.2662
-3.250 -0.0239 0.01708 0.00844 -0.0625 0.5894 0.2705
-3.000 0.0031 0.01680 0.00823 -0.0622 0.5783 0.2748
-2.750 0.0305 0.01671 0.00803 -0.0618 0.5691 0.2792
-2.500 0.0578 0.01659 0.00788 -0.0614 0.5584 0.2842
-2.250 0.0854 0.01658 0.00767 -0.0610 0.5496 0.2887
-2.000 0.1125 0.01625 0.00742 -0.0607 0.5398 0.2935
-1.750 0.1399 0.01616 0.00728 -0.0603 0.5308 0.2985
-1.500 0.1673 0.01612 0.00719 -0.0599 0.5217 0.3043
-1.250 0.1949 0.01605 0.00702 -0.0596 0.5129 0.3094
-1.000 0.2221 0.01590 0.00688 -0.0592 0.5050 0.3149
-0.750 0.2494 0.01583 0.00683 -0.0589 0.4959 0.3212
-0.500 0.2772 0.01589 0.00673 -0.0585 0.4884 0.3280
-0.250 0.3040 0.01571 0.00666 -0.0581 0.4799 0.3345
0.000 0.3313 0.01568 0.00661 -0.0578 0.4723 0.3420
0.250 0.3588 0.01573 0.00659 -0.0574 0.4649 0.3505
0.500 0.3855 0.01561 0.00658 -0.0570 0.4568 0.3598
0.750 0.4131 0.01569 0.00654 -0.0567 0.4502 0.3705
1.000 0.4395 0.01561 0.00662 -0.0563 0.4428 0.3820
1.250 0.4664 0.01558 0.00662 -0.0559 0.4356 0.3964
1.500 0.4936 0.01567 0.00666 -0.0555 0.4293 0.4147
1.750 0.5194 0.01559 0.00678 -0.0550 0.4222 0.4369
2.000 0.5455 0.01552 0.00685 -0.0545 0.4157 0.4665
2.250 0.5716 0.01555 0.00696 -0.0540 0.4099 0.5083
2.500 0.5956 0.01540 0.00715 -0.0531 0.4033 0.5694
2.750 0.6186 0.01523 0.00730 -0.0518 0.3974 0.6555
3.000 0.6399 0.01512 0.00749 -0.0499 0.3924 0.7676
3.250 0.6771 0.01500 0.00775 -0.0507 0.3855 0.9190
3.500 0.7314 0.01516 0.00783 -0.0559 0.3780 1.0000
3.750 0.7565 0.01551 0.00799 -0.0553 0.3729 1.0000
4.000 0.7798 0.01572 0.00824 -0.0544 0.3674 1.0000
4.250 0.8043 0.01595 0.00842 -0.0537 0.3621 1.0000
4.500 0.8297 0.01622 0.00857 -0.0531 0.3573 1.0000
4.750 0.8545 0.01658 0.00887 -0.0525 0.3523 1.0000
5.000 0.8785 0.01682 0.00914 -0.0517 0.3469 1.0000
5.250 0.9036 0.01708 0.00933 -0.0511 0.3421 1.0000
5.500 0.9299 0.01748 0.00958 -0.0508 0.3378 1.0000
5.750 0.9535 0.01783 0.00999 -0.0500 0.3332 1.0000
6.000 0.9775 0.01812 0.01031 -0.0493 0.3284 1.0000
6.250 1.0026 0.01841 0.01054 -0.0487 0.3239 1.0000
6.500 1.0292 0.01888 0.01086 -0.0485 0.3197 1.0000
6.750 1.0514 0.01923 0.01132 -0.0476 0.3154 1.0000
7.000 1.0748 0.01959 0.01171 -0.0468 0.3110 1.0000
7.250 1.0994 0.01993 0.01202 -0.0463 0.3070 1.0000
7.500 1.1254 0.02037 0.01236 -0.0459 0.3034 1.0000
7.750 1.1481 0.02089 0.01294 -0.0452 0.2996 1.0000
8.000 1.1695 0.02130 0.01342 -0.0442 0.2954 1.0000
8.250 1.1926 0.02167 0.01380 -0.0435 0.2915 1.0000
8.500 1.2173 0.02207 0.01415 -0.0430 0.2882 1.0000
8.750 1.2440 0.02276 0.01473 -0.0430 0.2848 1.0000
9.000 1.2619 0.02326 0.01541 -0.0415 0.2816 1.0000
9.250 1.2818 0.02377 0.01600 -0.0404 0.2780 1.0000
9.500 1.3037 0.02421 0.01645 -0.0396 0.2746 1.0000
9.750 1.3278 0.02463 0.01682 -0.0391 0.2715 1.0000
10.000 1.3550 0.02542 0.01750 -0.0393 0.2684 1.0000
10.250 1.3689 0.02605 0.01834 -0.0374 0.2657 1.0000
10.500 1.3849 0.02671 0.01912 -0.0359 0.2627 1.0000
10.750 1.4031 0.02729 0.01976 -0.0348 0.2597 1.0000
11.000 1.4243 0.02777 0.02023 -0.0340 0.2568 1.0000
11.250 1.4498 0.02831 0.02069 -0.0338 0.2541 1.0000
11.500 1.4701 0.02926 0.02168 -0.0331 0.2516 1.0000
11.750 1.4766 0.03011 0.02273 -0.0306 0.2491 1.0000
12.000 1.4849 0.03093 0.02368 -0.0283 0.2464 1.0000
12.250 1.4954 0.03163 0.02445 -0.0262 0.2437 1.0000
12.500 1.5114 0.03222 0.02505 -0.0248 0.2413 1.0000
12.750 1.5365 0.03275 0.02552 -0.0247 0.2389 1.0000
13.000 1.5576 0.03377 0.02654 -0.0243 0.2363 1.0000
13.250 1.5475 0.03499 0.02797 -0.0202 0.2343 1.0000
13.500 1.5398 0.03644 0.02959 -0.0170 0.2321 1.0000
13.750 1.5371 0.03787 0.03115 -0.0148 0.2297 1.0000
14.000 1.5436 0.03898 0.03232 -0.0134 0.2273 1.0000
14.250 1.5622 0.03959 0.03292 -0.0128 0.2249 1.0000
14.500 1.6015 0.03971 0.03290 -0.0136 0.2222 1.0000
14.750 1.5828 0.04217 0.03558 -0.0111 0.2203 1.0000
15.000 1.5542 0.04556 0.03922 -0.0091 0.2182 1.0000
15.250 1.5259 0.04956 0.04344 -0.0082 0.2158 1.0000
15.500 1.5082 0.05319 0.04721 -0.0081 0.2133 1.0000
15.750 1.5226 0.05411 0.04813 -0.0078 0.2109 1.0000
16.000 1.5741 0.05202 0.04587 -0.0072 0.2084 1.0000
16.250 1.5604 0.05564 0.04962 -0.0072 0.2062 1.0000
16.500 0.9287 0.15946 0.15453 -0.0556 0.1674 1.0000
16.750 0.9560 0.15805 0.15314 -0.0542 0.1667 1.0000
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Polar data table (+)
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