EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E1212 AIRFOIL (e1212-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.83 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1212-il-1000000.txt Download as CSV file: xf-e1212-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9006 0.08689 0.08334 -0.0403 1.0000 0.0199
-16.500 -0.9221 0.08045 0.07682 -0.0439 1.0000 0.0203
-16.250 -0.9449 0.07400 0.07029 -0.0475 1.0000 0.0203
-16.000 -0.9817 0.06611 0.06228 -0.0520 1.0000 0.0203
-15.750 -1.0230 0.05781 0.05383 -0.0568 1.0000 0.0202
-15.500 -1.0676 0.04910 0.04496 -0.0619 1.0000 0.0198
-15.250 -1.1256 0.03778 0.03339 -0.0694 1.0000 0.0195
-15.000 -1.1511 0.03016 0.02555 -0.0760 1.0000 0.0195
-14.750 -1.1629 0.02631 0.02155 -0.0784 1.0000 0.0197
-14.500 -1.1733 0.02424 0.01937 -0.0768 1.0000 0.0201
-14.250 -1.1832 0.02295 0.01801 -0.0728 1.0000 0.0206
-14.000 -1.1793 0.02184 0.01686 -0.0704 1.0000 0.0213
-13.750 -1.1704 0.02094 0.01592 -0.0682 1.0000 0.0223
-13.500 -1.1587 0.02015 0.01508 -0.0662 1.0000 0.0233
-13.250 -1.1475 0.01926 0.01416 -0.0642 1.0000 0.0248
-13.000 -1.1328 0.01857 0.01344 -0.0624 1.0000 0.0265
-12.750 -1.1186 0.01779 0.01265 -0.0606 1.0000 0.0287
-12.500 -1.1029 0.01708 0.01194 -0.0589 1.0000 0.0315
-12.250 -1.0862 0.01645 0.01130 -0.0572 1.0000 0.0345
-12.000 -1.0653 0.01577 0.01063 -0.0564 0.9996 0.0387
-11.750 -1.0281 0.01501 0.00990 -0.0587 0.9966 0.0445
-11.500 -0.9895 0.01431 0.00924 -0.0612 0.9929 0.0516
-11.250 -0.9554 0.01368 0.00863 -0.0627 0.9868 0.0583
-11.000 -0.9186 0.01306 0.00806 -0.0647 0.9793 0.0655
-10.750 -0.8877 0.01253 0.00756 -0.0654 0.9586 0.0723
-10.500 -0.8321 0.01192 0.00696 -0.0711 0.9298 0.0816
-10.250 -0.7983 0.01164 0.00652 -0.0721 0.8721 0.0883
-10.000 -0.7747 0.01149 0.00622 -0.0710 0.8321 0.0938
-9.750 -0.7507 0.01129 0.00593 -0.0701 0.8021 0.0997
-9.500 -0.7259 0.01109 0.00566 -0.0693 0.7775 0.1051
-9.250 -0.7000 0.01094 0.00542 -0.0687 0.7559 0.1104
-8.750 -0.6475 0.01061 0.00498 -0.0676 0.7182 0.1209
-8.500 -0.6211 0.01041 0.00476 -0.0671 0.7020 0.1264
-8.250 -0.5939 0.01030 0.00458 -0.0667 0.6863 0.1309
-8.000 -0.5670 0.01016 0.00439 -0.0662 0.6712 0.1361
-7.750 -0.5394 0.01004 0.00425 -0.0659 0.6572 0.1416
-7.500 -0.5118 0.00993 0.00409 -0.0655 0.6440 0.1470
-7.250 -0.4842 0.00986 0.00399 -0.0652 0.6304 0.1528
-7.000 -0.4558 0.00980 0.00388 -0.0649 0.6185 0.1566
-6.750 -0.4283 0.00968 0.00374 -0.0646 0.6064 0.1616
-6.500 -0.4000 0.00962 0.00364 -0.0643 0.5943 0.1656
-6.250 -0.3714 0.00960 0.00355 -0.0641 0.5837 0.1685
-6.000 -0.3436 0.00950 0.00341 -0.0638 0.5724 0.1725
-5.750 -0.3153 0.00942 0.00331 -0.0635 0.5619 0.1763
-5.500 -0.2870 0.00940 0.00324 -0.0633 0.5511 0.1796
-5.250 -0.2581 0.00938 0.00316 -0.0631 0.5418 0.1823
-5.000 -0.2299 0.00933 0.00306 -0.0628 0.5314 0.1853
-4.750 -0.2016 0.00923 0.00296 -0.0626 0.5220 0.1893
-4.500 -0.1732 0.00920 0.00289 -0.0624 0.5125 0.1926
-4.250 -0.1444 0.00919 0.00284 -0.0622 0.5039 0.1954
-4.000 -0.1156 0.00919 0.00278 -0.0620 0.4946 0.1977
-3.750 -0.0872 0.00915 0.00270 -0.0617 0.4857 0.2004
-3.500 -0.0588 0.00907 0.00261 -0.0615 0.4774 0.2045
-3.250 -0.0305 0.00907 0.00257 -0.0613 0.4685 0.2077
-3.000 -0.0015 0.00904 0.00253 -0.0612 0.4615 0.2106
-2.750 0.0271 0.00906 0.00249 -0.0610 0.4527 0.2131
-2.500 0.0560 0.00908 0.00247 -0.0608 0.4452 0.2147
-2.250 0.0842 0.00900 0.00238 -0.0606 0.4378 0.2192
-2.000 0.1124 0.00900 0.00235 -0.0603 0.4295 0.2231
-1.750 0.1414 0.00898 0.00233 -0.0602 0.4231 0.2264
-1.500 0.1699 0.00900 0.00231 -0.0600 0.4152 0.2292
-1.250 0.1986 0.00904 0.00231 -0.0598 0.4084 0.2314
-1.000 0.2272 0.00900 0.00227 -0.0597 0.4018 0.2359
-0.750 0.2553 0.00901 0.00226 -0.0595 0.3941 0.2403
-0.500 0.2840 0.00901 0.00226 -0.0593 0.3879 0.2443
-0.250 0.3127 0.00904 0.00226 -0.0591 0.3814 0.2480
0.000 0.3408 0.00911 0.00228 -0.0589 0.3738 0.2509
0.250 0.3694 0.00908 0.00227 -0.0588 0.3685 0.2572
0.500 0.3978 0.00910 0.00229 -0.0586 0.3624 0.2627
0.750 0.4258 0.00918 0.00233 -0.0583 0.3554 0.2674
1.000 0.4545 0.00917 0.00235 -0.0582 0.3507 0.2737
1.250 0.4827 0.00919 0.00238 -0.0580 0.3448 0.2811
1.500 0.5105 0.00928 0.00243 -0.0578 0.3382 0.2876
1.750 0.5389 0.00927 0.00247 -0.0576 0.3340 0.2981
2.000 0.5672 0.00931 0.00252 -0.0575 0.3291 0.3081
2.250 0.5949 0.00935 0.00259 -0.0572 0.3235 0.3219
2.500 0.6226 0.00940 0.00266 -0.0570 0.3181 0.3369
2.750 0.6508 0.00941 0.00272 -0.0568 0.3138 0.3550
3.000 0.6785 0.00944 0.00280 -0.0566 0.3090 0.3773
3.250 0.7055 0.00949 0.00291 -0.0563 0.3035 0.4055
3.500 0.7332 0.00949 0.00300 -0.0561 0.2999 0.4381
3.750 0.7608 0.00948 0.00310 -0.0558 0.2960 0.4762
4.000 0.7877 0.00949 0.00321 -0.0555 0.2914 0.5197
4.250 0.8138 0.00953 0.00336 -0.0551 0.2859 0.5705
4.500 0.8407 0.00948 0.00348 -0.0547 0.2826 0.6309
4.750 0.8666 0.00939 0.00361 -0.0542 0.2790 0.7088
5.000 0.8903 0.00929 0.00377 -0.0531 0.2751 0.8011
5.250 0.9110 0.00917 0.00396 -0.0512 0.2707 0.9263
5.500 0.9639 0.00932 0.00412 -0.0563 0.2664 1.0000
5.750 0.9899 0.00945 0.00424 -0.0558 0.2630 1.0000
6.000 1.0155 0.00962 0.00437 -0.0552 0.2589 1.0000
6.250 1.0404 0.00984 0.00454 -0.0545 0.2544 1.0000
6.500 1.0661 0.01000 0.00470 -0.0540 0.2512 1.0000
6.750 1.0923 0.01014 0.00484 -0.0536 0.2485 1.0000
7.000 1.1180 0.01031 0.00500 -0.0530 0.2451 1.0000
7.250 1.1430 0.01052 0.00518 -0.0524 0.2415 1.0000
7.500 1.1668 0.01081 0.00542 -0.0517 0.2369 1.0000
7.750 1.1930 0.01094 0.00557 -0.0513 0.2348 1.0000
8.000 1.2186 0.01111 0.00575 -0.0508 0.2319 1.0000
8.250 1.2433 0.01132 0.00594 -0.0502 0.2287 1.0000
8.500 1.2671 0.01157 0.00618 -0.0494 0.2253 1.0000
8.750 1.2897 0.01188 0.00646 -0.0485 0.2216 1.0000
9.000 1.3150 0.01205 0.00665 -0.0480 0.2198 1.0000
9.250 1.3394 0.01224 0.00686 -0.0474 0.2173 1.0000
9.500 1.3629 0.01248 0.00710 -0.0466 0.2145 1.0000
9.750 1.3851 0.01276 0.00737 -0.0457 0.2115 1.0000
10.000 1.4051 0.01314 0.00772 -0.0444 0.2079 1.0000
10.250 1.4276 0.01337 0.00798 -0.0435 0.2060 1.0000
10.500 1.4504 0.01358 0.00823 -0.0427 0.2041 1.0000
10.750 1.4717 0.01384 0.00850 -0.0416 0.2018 1.0000
11.000 1.4904 0.01414 0.00880 -0.0401 0.1994 1.0000
11.250 1.5058 0.01449 0.00916 -0.0381 0.1968 1.0000
11.500 1.5176 0.01496 0.00962 -0.0356 0.1937 1.0000
11.750 1.5351 0.01527 0.00996 -0.0340 0.1921 1.0000
12.000 1.5533 0.01556 0.01030 -0.0325 0.1904 1.0000
12.250 1.5700 0.01592 0.01069 -0.0310 0.1885 1.0000
12.500 1.5850 0.01635 0.01114 -0.0293 0.1862 1.0000
12.750 1.5978 0.01689 0.01169 -0.0274 0.1840 1.0000
13.000 1.6072 0.01760 0.01241 -0.0252 0.1813 1.0000
13.250 1.6175 0.01833 0.01317 -0.0234 0.1791 1.0000
13.500 1.6332 0.01886 0.01375 -0.0222 0.1778 1.0000
13.750 1.6474 0.01949 0.01443 -0.0210 0.1761 1.0000
14.000 1.6595 0.02027 0.01525 -0.0197 0.1741 1.0000
14.250 1.6695 0.02123 0.01623 -0.0184 0.1719 1.0000
14.500 1.6768 0.02243 0.01746 -0.0171 0.1697 1.0000
14.750 1.6795 0.02401 0.01907 -0.0157 0.1670 1.0000
15.000 1.6911 0.02508 0.02020 -0.0150 0.1657 1.0000
15.250 1.7029 0.02616 0.02135 -0.0144 0.1642 1.0000
15.500 1.7129 0.02743 0.02266 -0.0138 0.1623 1.0000
15.750 1.7199 0.02897 0.02425 -0.0132 0.1602 1.0000
16.000 1.7233 0.03086 0.02618 -0.0126 0.1580 1.0000
16.250 1.7227 0.03316 0.02851 -0.0121 0.1558 1.0000
16.500 1.7244 0.03530 0.03071 -0.0118 0.1537 1.0000
16.750 1.7324 0.03693 0.03241 -0.0116 0.1520 1.0000
17.000 1.7367 0.03891 0.03446 -0.0114 0.1501 1.0000
17.250 1.7368 0.04136 0.03695 -0.0113 0.1479 1.0000
17.500 1.7335 0.04419 0.03983 -0.0114 0.1459 1.0000
17.750 1.7243 0.04771 0.04339 -0.0117 0.1433 1.0000
18.000 1.7231 0.05049 0.04625 -0.0120 0.1416 1.0000
18.250 1.7249 0.05300 0.04883 -0.0123 0.1397 1.0000
18.500 1.7225 0.05600 0.05189 -0.0127 0.1373 1.0000
18.750 1.7141 0.05977 0.05571 -0.0135 0.1348 1.0000
19.000 1.6992 0.06438 0.06037 -0.0146 0.1320 1.0000
19.250 1.6946 0.06786 0.06392 -0.0155 0.1300 1.0000
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