EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E1212 AIRFOIL (e1212-il) Reynolds number: 500,000 Max Cl/Cd: 84.75 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1212-il-500000.txt Download as CSV file: xf-e1212-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8400 0.09085 0.08673 -0.0391 1.0000 0.0301
-16.250 -0.8479 0.08640 0.08228 -0.0413 1.0000 0.0308
-16.000 -0.8598 0.08133 0.07718 -0.0440 1.0000 0.0317
-15.750 -0.8715 0.07642 0.07222 -0.0465 1.0000 0.0326
-15.500 -0.8850 0.07141 0.06714 -0.0492 1.0000 0.0332
-15.250 -0.9073 0.06554 0.06120 -0.0523 1.0000 0.0338
-15.000 -0.9356 0.05902 0.05460 -0.0559 1.0000 0.0340
-14.750 -0.9680 0.05199 0.04746 -0.0599 1.0000 0.0341
-14.500 -1.0030 0.04446 0.03978 -0.0642 1.0000 0.0341
-14.250 -1.0340 0.03675 0.03190 -0.0695 1.0000 0.0341
-14.000 -1.0585 0.03001 0.02495 -0.0751 1.0000 0.0345
-13.750 -1.0768 0.02666 0.02147 -0.0754 1.0000 0.0352
-13.500 -1.0887 0.02507 0.01981 -0.0720 1.0000 0.0364
-13.250 -1.0894 0.02372 0.01839 -0.0693 1.0000 0.0385
-13.000 -1.0849 0.02249 0.01713 -0.0671 1.0000 0.0412
-12.750 -1.0774 0.02136 0.01598 -0.0649 1.0000 0.0445
-12.500 -1.0668 0.02037 0.01496 -0.0629 1.0000 0.0487
-12.250 -1.0541 0.01947 0.01405 -0.0611 1.0000 0.0534
-12.000 -1.0398 0.01866 0.01324 -0.0593 1.0000 0.0588
-11.750 -1.0242 0.01792 0.01250 -0.0577 1.0000 0.0645
-11.500 -1.0076 0.01727 0.01185 -0.0560 1.0000 0.0704
-11.250 -0.9905 0.01667 0.01127 -0.0544 1.0000 0.0764
-11.000 -0.9734 0.01611 0.01073 -0.0528 1.0000 0.0822
-10.750 -0.9323 0.01552 0.01016 -0.0557 0.9955 0.0905
-10.500 -0.8916 0.01499 0.00964 -0.0584 0.9897 0.0984
-10.250 -0.8520 0.01451 0.00917 -0.0609 0.9813 0.1058
-9.750 -0.7756 0.01369 0.00834 -0.0648 0.9466 0.1194
-9.500 -0.7244 0.01326 0.00789 -0.0693 0.9232 0.1265
-9.250 -0.6806 0.01302 0.00750 -0.0721 0.8851 0.1328
-9.000 -0.6534 0.01289 0.00725 -0.0717 0.8469 0.1384
-8.750 -0.6273 0.01289 0.00706 -0.0710 0.8171 0.1436
-8.500 -0.6025 0.01276 0.00689 -0.0702 0.7918 0.1493
-8.250 -0.5760 0.01277 0.00676 -0.0696 0.7698 0.1545
-8.000 -0.5503 0.01265 0.00657 -0.0689 0.7500 0.1593
-7.750 -0.5239 0.01262 0.00646 -0.0683 0.7320 0.1638
-7.500 -0.4969 0.01263 0.00632 -0.0678 0.7147 0.1679
-7.250 -0.4704 0.01246 0.00609 -0.0672 0.6987 0.1720
-7.000 -0.4435 0.01239 0.00598 -0.0668 0.6838 0.1759
-6.750 -0.4162 0.01237 0.00586 -0.0663 0.6697 0.1798
-6.500 -0.3885 0.01237 0.00573 -0.0659 0.6556 0.1830
-6.250 -0.3618 0.01215 0.00550 -0.0655 0.6429 0.1871
-6.000 -0.3346 0.01210 0.00539 -0.0650 0.6303 0.1906
-5.750 -0.3066 0.01206 0.00529 -0.0647 0.6178 0.1942
-5.500 -0.2787 0.01206 0.00517 -0.0643 0.6064 0.1974
-5.250 -0.2513 0.01189 0.00495 -0.0640 0.5949 0.2009
-5.000 -0.2239 0.01178 0.00482 -0.0636 0.5840 0.2045
-4.750 -0.1960 0.01174 0.00473 -0.0633 0.5729 0.2079
-4.500 -0.1679 0.01171 0.00464 -0.0630 0.5629 0.2113
-4.250 -0.1398 0.01171 0.00454 -0.0626 0.5524 0.2140
-4.000 -0.1123 0.01153 0.00434 -0.0623 0.5428 0.2178
-3.750 -0.0847 0.01144 0.00422 -0.0620 0.5327 0.2213
-3.500 -0.0566 0.01140 0.00415 -0.0617 0.5239 0.2246
-3.250 -0.0284 0.01138 0.00407 -0.0614 0.5144 0.2281
-3.000 -0.0003 0.01140 0.00400 -0.0611 0.5055 0.2309
-2.750 0.0276 0.01126 0.00385 -0.0608 0.4964 0.2344
-2.500 0.0550 0.01121 0.00376 -0.0605 0.4880 0.2385
-2.250 0.0834 0.01115 0.00371 -0.0603 0.4800 0.2422
-2.000 0.1113 0.01115 0.00365 -0.0600 0.4714 0.2457
-1.750 0.1397 0.01116 0.00361 -0.0597 0.4635 0.2490
-1.500 0.1675 0.01108 0.00351 -0.0594 0.4554 0.2532
-1.250 0.1949 0.01106 0.00347 -0.0591 0.4479 0.2576
-1.000 0.2233 0.01102 0.00344 -0.0589 0.4405 0.2620
-0.750 0.2512 0.01106 0.00342 -0.0586 0.4326 0.2663
-0.500 0.2793 0.01107 0.00340 -0.0584 0.4257 0.2703
-0.250 0.3070 0.01100 0.00336 -0.0581 0.4186 0.2761
0.000 0.3344 0.01105 0.00337 -0.0577 0.4112 0.2818
0.250 0.3628 0.01106 0.00337 -0.0575 0.4047 0.2871
0.500 0.3904 0.01104 0.00336 -0.0573 0.3979 0.2938
0.750 0.4176 0.01109 0.00339 -0.0569 0.3913 0.3010
1.000 0.4460 0.01110 0.00342 -0.0567 0.3851 0.3083
1.250 0.4733 0.01109 0.00344 -0.0564 0.3786 0.3186
1.500 0.5005 0.01119 0.00350 -0.0561 0.3725 0.3289
1.750 0.5284 0.01114 0.00355 -0.0558 0.3671 0.3428
2.000 0.5557 0.01116 0.00360 -0.0555 0.3610 0.3589
2.250 0.5822 0.01124 0.00370 -0.0551 0.3548 0.3792
2.500 0.6099 0.01120 0.00378 -0.0549 0.3500 0.4071
2.750 0.6369 0.01118 0.00387 -0.0546 0.3446 0.4416
3.000 0.6630 0.01121 0.00399 -0.0541 0.3394 0.4834
3.250 0.6893 0.01119 0.00413 -0.0537 0.3346 0.5347
3.500 0.7155 0.01111 0.00426 -0.0532 0.3296 0.5957
3.750 0.7402 0.01105 0.00440 -0.0524 0.3245 0.6705
4.000 0.7623 0.01102 0.00461 -0.0510 0.3194 0.7614
4.250 0.7833 0.01079 0.00477 -0.0490 0.3158 0.8825
4.500 0.8427 0.01089 0.00494 -0.0552 0.3097 1.0000
4.750 0.8670 0.01110 0.00508 -0.0544 0.3052 1.0000
5.000 0.8915 0.01133 0.00526 -0.0537 0.3008 1.0000
5.250 0.9174 0.01146 0.00540 -0.0531 0.2968 1.0000
5.500 0.9426 0.01164 0.00555 -0.0525 0.2924 1.0000
5.750 0.9671 0.01188 0.00573 -0.0518 0.2882 1.0000
6.000 0.9914 0.01215 0.00596 -0.0511 0.2842 1.0000
6.250 1.0172 0.01231 0.00613 -0.0506 0.2808 1.0000
6.500 1.0424 0.01250 0.00632 -0.0500 0.2769 1.0000
6.750 1.0667 0.01275 0.00652 -0.0493 0.2729 1.0000
7.000 1.0896 0.01311 0.00682 -0.0484 0.2685 1.0000
7.250 1.1150 0.01327 0.00702 -0.0479 0.2655 1.0000
7.500 1.1398 0.01347 0.00724 -0.0473 0.2621 1.0000
7.750 1.1636 0.01373 0.00748 -0.0465 0.2586 1.0000
8.000 1.1861 0.01405 0.00776 -0.0456 0.2551 1.0000
8.250 1.2085 0.01442 0.00810 -0.0447 0.2517 1.0000
8.500 1.2324 0.01463 0.00836 -0.0440 0.2489 1.0000
8.750 1.2556 0.01487 0.00863 -0.0432 0.2457 1.0000
9.000 1.2774 0.01517 0.00892 -0.0422 0.2424 1.0000
9.250 1.2978 0.01556 0.00927 -0.0411 0.2392 1.0000
9.500 1.3178 0.01599 0.00969 -0.0399 0.2362 1.0000
9.750 1.3393 0.01625 0.01002 -0.0388 0.2340 1.0000
10.000 1.3595 0.01655 0.01036 -0.0376 0.2314 1.0000
10.250 1.3772 0.01687 0.01069 -0.0360 0.2287 1.0000
10.500 1.3929 0.01726 0.01108 -0.0341 0.2260 1.0000
10.750 1.4073 0.01777 0.01156 -0.0322 0.2233 1.0000
11.000 1.4230 0.01827 0.01208 -0.0305 0.2209 1.0000
11.250 1.4394 0.01866 0.01254 -0.0289 0.2189 1.0000
11.500 1.4551 0.01909 0.01303 -0.0273 0.2167 1.0000
11.750 1.4698 0.01958 0.01355 -0.0257 0.2144 1.0000
12.000 1.4834 0.02016 0.01414 -0.0241 0.2121 1.0000
12.250 1.4953 0.02087 0.01484 -0.0224 0.2096 1.0000
12.500 1.5075 0.02170 0.01566 -0.0209 0.2069 1.0000
12.750 1.5204 0.02236 0.01642 -0.0195 0.2053 1.0000
13.000 1.5327 0.02312 0.01725 -0.0183 0.2033 1.0000
13.250 1.5445 0.02396 0.01816 -0.0171 0.2011 1.0000
13.500 1.5552 0.02490 0.01914 -0.0160 0.1989 1.0000
13.750 1.5648 0.02597 0.02023 -0.0149 0.1968 1.0000
14.000 1.5737 0.02717 0.02141 -0.0138 0.1942 1.0000
14.250 1.5834 0.02835 0.02265 -0.0129 0.1921 1.0000
14.500 1.5921 0.02963 0.02403 -0.0122 0.1903 1.0000
14.750 1.6004 0.03099 0.02547 -0.0116 0.1882 1.0000
15.000 1.6079 0.03245 0.02699 -0.0110 0.1861 1.0000
15.250 1.6145 0.03403 0.02861 -0.0105 0.1841 1.0000
15.500 1.6199 0.03573 0.03031 -0.0100 0.1818 1.0000
15.750 1.6268 0.03730 0.03189 -0.0095 0.1793 1.0000
16.000 1.6304 0.03931 0.03402 -0.0093 0.1776 1.0000
16.250 1.6339 0.04136 0.03618 -0.0093 0.1757 1.0000
16.500 1.6363 0.04355 0.03844 -0.0093 0.1735 1.0000
16.750 1.6383 0.04584 0.04079 -0.0094 0.1713 1.0000
17.000 1.6400 0.04817 0.04313 -0.0095 0.1690 1.0000
17.250 1.6443 0.05016 0.04512 -0.0094 0.1664 1.0000
17.500 1.6421 0.05318 0.04828 -0.0100 0.1647 1.0000
17.750 1.6402 0.05621 0.05142 -0.0107 0.1625 1.0000
18.000 1.6381 0.05931 0.05460 -0.0114 0.1601 1.0000
18.250 1.6366 0.06233 0.05766 -0.0122 0.1577 1.0000
18.500 1.6361 0.06517 0.06049 -0.0127 0.1549 1.0000
18.750 1.6324 0.06864 0.06406 -0.0138 0.1529 1.0000
19.000 1.6254 0.07265 0.06820 -0.0152 0.1504 1.0000
19.250 1.6188 0.07665 0.07230 -0.0166 0.1479 1.0000
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