EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E1212 AIRFOIL (e1212-il) Reynolds number: 500,000 Max Cl/Cd: 85.46 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1212-il-500000-n5.txt Download as CSV file: xf-e1212-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8303 0.08938 0.08517 -0.0392 1.0000 0.0231
-16.000 -0.8445 0.08387 0.07960 -0.0421 1.0000 0.0236
-15.750 -0.8609 0.07819 0.07385 -0.0452 1.0000 0.0240
-15.500 -0.8783 0.07259 0.06818 -0.0482 1.0000 0.0242
-15.250 -0.9037 0.06621 0.06171 -0.0517 1.0000 0.0245
-15.000 -0.9334 0.05941 0.05480 -0.0555 1.0000 0.0245
-14.750 -0.9688 0.05193 0.04719 -0.0597 1.0000 0.0245
-14.500 -1.0077 0.04378 0.03887 -0.0645 1.0000 0.0243
-14.250 -1.0388 0.03587 0.03075 -0.0701 1.0000 0.0242
-14.000 -1.0591 0.02986 0.02454 -0.0750 1.0000 0.0245
-13.750 -1.0725 0.02692 0.02147 -0.0752 1.0000 0.0250
-13.500 -1.0815 0.02543 0.01990 -0.0722 1.0000 0.0257
-13.250 -1.0812 0.02422 0.01863 -0.0695 1.0000 0.0268
-13.000 -1.0749 0.02315 0.01751 -0.0674 1.0000 0.0281
-12.750 -1.0646 0.02226 0.01657 -0.0655 1.0000 0.0298
-12.500 -1.0537 0.02134 0.01562 -0.0636 1.0000 0.0318
-12.250 -1.0401 0.02057 0.01482 -0.0618 1.0000 0.0339
-12.000 -1.0171 0.01970 0.01393 -0.0618 0.9977 0.0370
-11.750 -0.9859 0.01882 0.01303 -0.0634 0.9897 0.0411
-11.500 -0.9569 0.01802 0.01222 -0.0643 0.9774 0.0454
-11.250 -0.9238 0.01724 0.01142 -0.0659 0.9523 0.0507
-11.000 -0.8682 0.01631 0.01047 -0.0720 0.9189 0.0588
-10.750 -0.8295 0.01567 0.00970 -0.0744 0.8682 0.0664
-10.500 -0.8069 0.01530 0.00919 -0.0735 0.8288 0.0724
-10.000 -0.7617 0.01465 0.00832 -0.0715 0.7749 0.0841
-9.750 -0.7383 0.01432 0.00791 -0.0707 0.7539 0.0899
-9.500 -0.7141 0.01403 0.00755 -0.0700 0.7344 0.0954
-9.250 -0.6892 0.01379 0.00722 -0.0693 0.7162 0.1011
-9.000 -0.6642 0.01350 0.00689 -0.0687 0.6996 0.1076
-8.750 -0.6387 0.01325 0.00660 -0.0681 0.6844 0.1142
-8.500 -0.6128 0.01306 0.00633 -0.0676 0.6697 0.1213
-8.250 -0.5868 0.01283 0.00609 -0.0671 0.6555 0.1283
-8.000 -0.5602 0.01266 0.00586 -0.0666 0.6423 0.1342
-7.750 -0.5336 0.01251 0.00566 -0.0661 0.6296 0.1398
-7.500 -0.5064 0.01238 0.00545 -0.0658 0.6169 0.1442
-7.250 -0.4795 0.01224 0.00528 -0.0653 0.6054 0.1489
-7.000 -0.4520 0.01213 0.00510 -0.0650 0.5934 0.1534
-6.750 -0.4245 0.01203 0.00493 -0.0646 0.5828 0.1569
-6.500 -0.3972 0.01191 0.00477 -0.0642 0.5713 0.1609
-6.250 -0.3695 0.01182 0.00463 -0.0639 0.5613 0.1649
-6.000 -0.3416 0.01176 0.00448 -0.0636 0.5508 0.1683
-5.750 -0.3139 0.01165 0.00433 -0.0633 0.5411 0.1716
-5.500 -0.2862 0.01157 0.00421 -0.0629 0.5309 0.1752
-5.250 -0.2582 0.01150 0.00410 -0.0627 0.5222 0.1788
-5.000 -0.2301 0.01146 0.00398 -0.0624 0.5123 0.1819
-4.750 -0.2021 0.01139 0.00386 -0.0621 0.5035 0.1847
-4.500 -0.1742 0.01131 0.00375 -0.0618 0.4943 0.1880
-4.250 -0.1463 0.01127 0.00366 -0.0615 0.4862 0.1913
-4.000 -0.1180 0.01122 0.00357 -0.0613 0.4774 0.1946
-3.500 -0.0616 0.01115 0.00340 -0.0607 0.4613 0.2000
-3.250 -0.0337 0.01110 0.00332 -0.0605 0.4533 0.2034
-3.000 -0.0056 0.01107 0.00326 -0.0602 0.4457 0.2064
-2.750 0.0227 0.01105 0.00321 -0.0600 0.4376 0.2097
-2.250 0.0793 0.01104 0.00310 -0.0595 0.4239 0.2151
-2.000 0.1072 0.01100 0.00305 -0.0592 0.4164 0.2186
-1.750 0.1351 0.01100 0.00302 -0.0589 0.4093 0.2223
-1.500 0.1635 0.01098 0.00300 -0.0587 0.4025 0.2258
-1.250 0.1916 0.01100 0.00297 -0.0585 0.3958 0.2290
-1.000 0.2198 0.01104 0.00296 -0.0582 0.3896 0.2319
-0.750 0.2479 0.01101 0.00294 -0.0580 0.3829 0.2360
-0.500 0.2757 0.01103 0.00294 -0.0577 0.3760 0.2399
-0.250 0.3038 0.01105 0.00295 -0.0575 0.3705 0.2442
0.000 0.3320 0.01108 0.00296 -0.0573 0.3643 0.2484
0.250 0.3598 0.01112 0.00297 -0.0570 0.3578 0.2524
0.500 0.3876 0.01114 0.00300 -0.0568 0.3523 0.2572
0.750 0.4157 0.01117 0.00303 -0.0565 0.3468 0.2625
1.000 0.4434 0.01123 0.00307 -0.0563 0.3406 0.2679
1.250 0.4710 0.01128 0.00312 -0.0560 0.3353 0.2742
1.500 0.4989 0.01131 0.00317 -0.0558 0.3303 0.2811
1.750 0.5266 0.01137 0.00323 -0.0555 0.3251 0.2878
2.000 0.5537 0.01145 0.00330 -0.0552 0.3198 0.2959
2.250 0.5815 0.01149 0.00337 -0.0549 0.3152 0.3055
2.500 0.6090 0.01153 0.00345 -0.0547 0.3101 0.3170
3.000 0.6631 0.01169 0.00366 -0.0540 0.3012 0.3444
3.250 0.6906 0.01173 0.00376 -0.0538 0.2973 0.3607
3.500 0.7176 0.01179 0.00387 -0.0535 0.2925 0.3797
3.750 0.7441 0.01187 0.00400 -0.0531 0.2877 0.4041
4.000 0.7706 0.01194 0.00414 -0.0527 0.2837 0.4332
4.250 0.7973 0.01196 0.00428 -0.0524 0.2801 0.4676
4.500 0.8237 0.01200 0.00443 -0.0520 0.2761 0.5048
4.750 0.8494 0.01206 0.00460 -0.0515 0.2722 0.5479
5.000 0.8744 0.01212 0.00479 -0.0509 0.2683 0.5993
5.250 0.8996 0.01208 0.00497 -0.0502 0.2650 0.6661
5.500 0.9231 0.01202 0.00516 -0.0492 0.2611 0.7459
5.750 0.9435 0.01194 0.00536 -0.0475 0.2573 0.8443
6.000 0.9893 0.01206 0.00562 -0.0509 0.2528 1.0000
6.250 1.0147 0.01223 0.00580 -0.0504 0.2501 1.0000
6.500 1.0399 0.01242 0.00598 -0.0498 0.2469 1.0000
6.750 1.0646 0.01264 0.00618 -0.0492 0.2433 1.0000
7.000 1.0885 0.01290 0.00641 -0.0484 0.2396 1.0000
7.250 1.1122 0.01316 0.00665 -0.0477 0.2363 1.0000
7.500 1.1370 0.01337 0.00686 -0.0470 0.2336 1.0000
7.750 1.1611 0.01360 0.00710 -0.0464 0.2306 1.0000
8.000 1.1845 0.01386 0.00736 -0.0456 0.2276 1.0000
8.250 1.2071 0.01415 0.00763 -0.0447 0.2247 1.0000
8.500 1.2288 0.01448 0.00794 -0.0437 0.2217 1.0000
8.750 1.2521 0.01471 0.00820 -0.0429 0.2194 1.0000
9.000 1.2745 0.01498 0.00849 -0.0420 0.2165 1.0000
9.250 1.2958 0.01528 0.00880 -0.0409 0.2136 1.0000
9.500 1.3160 0.01562 0.00914 -0.0398 0.2110 1.0000
9.750 1.3343 0.01599 0.00950 -0.0383 0.2085 1.0000
10.000 1.3513 0.01634 0.00987 -0.0365 0.2064 1.0000
10.250 1.3693 0.01665 0.01022 -0.0350 0.2045 1.0000
10.500 1.3863 0.01700 0.01061 -0.0333 0.2021 1.0000
10.750 1.4022 0.01741 0.01104 -0.0316 0.1998 1.0000
11.000 1.4169 0.01788 0.01152 -0.0298 0.1974 1.0000
11.250 1.4303 0.01842 0.01207 -0.0280 0.1953 1.0000
11.500 1.4422 0.01905 0.01271 -0.0260 0.1931 1.0000
11.750 1.4578 0.01956 0.01328 -0.0247 0.1914 1.0000
12.000 1.4722 0.02015 0.01392 -0.0233 0.1894 1.0000
12.250 1.4851 0.02084 0.01466 -0.0218 0.1873 1.0000
12.500 1.4968 0.02164 0.01551 -0.0205 0.1852 1.0000
12.750 1.5066 0.02260 0.01649 -0.0191 0.1830 1.0000
13.000 1.5148 0.02373 0.01764 -0.0178 0.1809 1.0000
13.250 1.5241 0.02486 0.01881 -0.0167 0.1789 1.0000
13.500 1.5360 0.02588 0.01991 -0.0159 0.1771 1.0000
13.750 1.5463 0.02706 0.02115 -0.0151 0.1751 1.0000
14.000 1.5546 0.02843 0.02257 -0.0144 0.1728 1.0000
14.250 1.5610 0.03000 0.02419 -0.0137 0.1706 1.0000
14.500 1.5653 0.03181 0.02603 -0.0131 0.1684 1.0000
14.750 1.5685 0.03376 0.02802 -0.0126 0.1664 1.0000
15.000 1.5768 0.03534 0.02968 -0.0123 0.1647 1.0000
15.250 1.5830 0.03712 0.03154 -0.0120 0.1629 1.0000
15.500 1.5868 0.03916 0.03364 -0.0118 0.1606 1.0000
15.750 1.5886 0.04143 0.03597 -0.0117 0.1585 1.0000
16.000 1.5874 0.04405 0.03863 -0.0117 0.1563 1.0000
16.250 1.5842 0.04693 0.04154 -0.0119 0.1542 1.0000
16.500 1.5880 0.04919 0.04390 -0.0121 0.1524 1.0000
16.750 1.5893 0.05177 0.04657 -0.0124 0.1503 1.0000
17.000 1.5879 0.05468 0.04955 -0.0128 0.1478 1.0000
17.250 1.5844 0.05791 0.05284 -0.0134 0.1456 1.0000
17.500 1.5778 0.06158 0.05655 -0.0143 0.1433 1.0000
17.750 1.5751 0.06486 0.05991 -0.0150 0.1413 1.0000
18.000 1.5734 0.06807 0.06321 -0.0159 0.1388 1.0000
18.250 1.5689 0.07171 0.06692 -0.0169 0.1363 1.0000
18.500 1.5598 0.07600 0.07127 -0.0183 0.1336 1.0000
18.750 1.5499 0.08045 0.07577 -0.0198 0.1312 1.0000
19.000 1.5471 0.08405 0.07946 -0.0210 0.1287 1.0000
19.250 1.5388 0.08847 0.08396 -0.0226 0.1257 1.0000
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