EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E1212 AIRFOIL (e1212-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.54 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1212-il-1000000-n5.txt Download as CSV file: xf-e1212-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9108 0.08534 0.08164 -0.0412 1.0000 0.0148
-16.500 -0.9314 0.07904 0.07526 -0.0447 1.0000 0.0150
-16.250 -0.9527 0.07289 0.06901 -0.0481 1.0000 0.0150
-16.000 -0.9914 0.06475 0.06074 -0.0528 1.0000 0.0150
-15.750 -1.0365 0.05599 0.05182 -0.0579 1.0000 0.0148
-15.250 -1.1320 0.03663 0.03203 -0.0703 1.0000 0.0144
-14.750 -1.1655 0.02605 0.02111 -0.0783 1.0000 0.0146
-14.500 -1.1739 0.02418 0.01915 -0.0766 1.0000 0.0149
-14.250 -1.1798 0.02308 0.01799 -0.0729 1.0000 0.0152
-14.000 -1.1743 0.02210 0.01696 -0.0706 1.0000 0.0156
-13.750 -1.1646 0.02127 0.01609 -0.0685 1.0000 0.0161
-13.500 -1.1523 0.02054 0.01532 -0.0666 1.0000 0.0167
-13.250 -1.1346 0.01979 0.01453 -0.0656 0.9994 0.0174
-13.000 -1.1041 0.01895 0.01367 -0.0671 0.9955 0.0186
-12.750 -1.0763 0.01826 0.01295 -0.0677 0.9886 0.0197
-12.500 -1.0489 0.01751 0.01219 -0.0683 0.9777 0.0214
-12.250 -1.0055 0.01675 0.01140 -0.0720 0.9501 0.0234
-12.000 -0.9540 0.01600 0.01045 -0.0772 0.8743 0.0269
-11.750 -0.9351 0.01567 0.00994 -0.0756 0.8262 0.0291
-11.500 -0.9152 0.01526 0.00941 -0.0743 0.7946 0.0320
-11.250 -0.8938 0.01486 0.00893 -0.0733 0.7686 0.0351
-11.000 -0.8714 0.01447 0.00846 -0.0724 0.7472 0.0384
-10.750 -0.8485 0.01408 0.00801 -0.0715 0.7280 0.0425
-10.250 -0.8012 0.01334 0.00716 -0.0700 0.6933 0.0518
-10.000 -0.7767 0.01297 0.00676 -0.0694 0.6774 0.0571
-9.750 -0.7519 0.01263 0.00639 -0.0688 0.6634 0.0628
-9.500 -0.7268 0.01231 0.00604 -0.0682 0.6493 0.0687
-9.250 -0.7013 0.01200 0.00571 -0.0676 0.6355 0.0753
-9.000 -0.6754 0.01171 0.00540 -0.0672 0.6234 0.0816
-8.500 -0.6225 0.01122 0.00487 -0.0663 0.5993 0.0940
-8.250 -0.5958 0.01102 0.00463 -0.0659 0.5874 0.0997
-8.000 -0.5689 0.01080 0.00441 -0.0655 0.5763 0.1059
-7.750 -0.5418 0.01062 0.00420 -0.0651 0.5660 0.1128
-7.500 -0.5144 0.01044 0.00401 -0.0648 0.5553 0.1202
-7.250 -0.4872 0.01025 0.00383 -0.0644 0.5452 0.1283
-7.000 -0.4594 0.01012 0.00367 -0.0642 0.5355 0.1340
-6.750 -0.4316 0.01000 0.00353 -0.0639 0.5257 0.1395
-6.500 -0.4034 0.00992 0.00341 -0.0636 0.5159 0.1434
-6.250 -0.3755 0.00981 0.00328 -0.0633 0.5069 0.1480
-6.000 -0.3471 0.00972 0.00317 -0.0631 0.4983 0.1522
-5.500 -0.2904 0.00959 0.00296 -0.0626 0.4804 0.1591
-5.250 -0.2621 0.00953 0.00287 -0.0624 0.4717 0.1630
-5.000 -0.2336 0.00948 0.00279 -0.0622 0.4641 0.1664
-4.750 -0.2049 0.00945 0.00271 -0.0620 0.4550 0.1689
-4.500 -0.1766 0.00940 0.00263 -0.0617 0.4475 0.1724
-4.250 -0.1479 0.00934 0.00256 -0.0616 0.4407 0.1759
-4.000 -0.1194 0.00932 0.00250 -0.0614 0.4324 0.1790
-3.750 -0.0907 0.00930 0.00245 -0.0612 0.4253 0.1816
-3.500 -0.0619 0.00929 0.00239 -0.0610 0.4179 0.1837
-3.000 -0.0048 0.00922 0.00230 -0.0606 0.4050 0.1904
-2.750 0.0238 0.00922 0.00226 -0.0604 0.3974 0.1936
-2.500 0.0524 0.00923 0.00223 -0.0602 0.3903 0.1961
-2.250 0.0813 0.00922 0.00220 -0.0601 0.3846 0.1980
-2.000 0.1099 0.00922 0.00217 -0.0599 0.3780 0.2013
-1.750 0.1384 0.00922 0.00216 -0.0597 0.3715 0.2047
-1.500 0.1671 0.00921 0.00214 -0.0596 0.3653 0.2077
-1.250 0.1956 0.00924 0.00214 -0.0594 0.3588 0.2108
-1.000 0.2243 0.00927 0.00214 -0.0592 0.3532 0.2134
-0.750 0.2530 0.00928 0.00213 -0.0591 0.3473 0.2156
-0.500 0.2813 0.00930 0.00214 -0.0589 0.3408 0.2198
-0.250 0.3098 0.00933 0.00215 -0.0587 0.3355 0.2238
0.000 0.3384 0.00934 0.00217 -0.0585 0.3303 0.2272
0.250 0.3668 0.00939 0.00219 -0.0584 0.3243 0.2301
0.500 0.3951 0.00945 0.00222 -0.0582 0.3188 0.2333
0.750 0.4237 0.00946 0.00224 -0.0580 0.3149 0.2384
1.000 0.4520 0.00950 0.00228 -0.0578 0.3096 0.2427
1.250 0.4801 0.00957 0.00233 -0.0576 0.3039 0.2467
1.500 0.5085 0.00962 0.00237 -0.0575 0.2996 0.2502
1.750 0.5368 0.00964 0.00242 -0.0573 0.2957 0.2571
2.000 0.5649 0.00970 0.00247 -0.0571 0.2913 0.2634
2.250 0.5928 0.00978 0.00254 -0.0569 0.2864 0.2684
2.500 0.6209 0.00983 0.00261 -0.0567 0.2825 0.2756
2.750 0.6490 0.00988 0.00268 -0.0565 0.2782 0.2833
3.000 0.6768 0.00996 0.00275 -0.0563 0.2738 0.2913
3.250 0.7043 0.01003 0.00285 -0.0560 0.2695 0.3030
3.500 0.7322 0.01008 0.00294 -0.0558 0.2665 0.3149
3.750 0.7600 0.01014 0.00302 -0.0556 0.2632 0.3279
4.000 0.7874 0.01020 0.00313 -0.0554 0.2592 0.3433
4.250 0.8145 0.01029 0.00325 -0.0551 0.2547 0.3601
4.500 0.8417 0.01036 0.00336 -0.0548 0.2510 0.3800
4.750 0.8691 0.01040 0.00348 -0.0546 0.2481 0.4069
5.000 0.8961 0.01046 0.00361 -0.0543 0.2447 0.4363
5.250 0.9227 0.01052 0.00375 -0.0539 0.2411 0.4682
5.500 0.9490 0.01061 0.00391 -0.0536 0.2372 0.5021
6.000 1.0020 0.01067 0.00421 -0.0528 0.2315 0.5931
6.250 1.0276 0.01069 0.00439 -0.0523 0.2279 0.6540
6.500 1.0522 0.01072 0.00458 -0.0517 0.2244 0.7214
6.750 1.0760 0.01073 0.00478 -0.0508 0.2214 0.7937
7.000 1.0959 0.01059 0.00496 -0.0489 0.2194 0.9087
7.250 1.1398 0.01073 0.00517 -0.0521 0.2162 1.0000
7.500 1.1650 0.01093 0.00535 -0.0515 0.2131 1.0000
7.750 1.1896 0.01115 0.00555 -0.0509 0.2098 1.0000
8.000 1.2142 0.01138 0.00576 -0.0503 0.2067 1.0000
8.250 1.2393 0.01156 0.00595 -0.0497 0.2045 1.0000
8.500 1.2641 0.01176 0.00615 -0.0491 0.2022 1.0000
8.750 1.2883 0.01198 0.00636 -0.0485 0.1997 1.0000
9.000 1.3119 0.01223 0.00660 -0.0477 0.1970 1.0000
9.250 1.3348 0.01250 0.00687 -0.0469 0.1942 1.0000
9.500 1.3582 0.01273 0.00711 -0.0461 0.1921 1.0000
9.750 1.3816 0.01295 0.00735 -0.0453 0.1902 1.0000
10.000 1.4042 0.01320 0.00760 -0.0445 0.1879 1.0000
10.250 1.4261 0.01347 0.00787 -0.0435 0.1857 1.0000
10.500 1.4467 0.01377 0.00818 -0.0423 0.1832 1.0000
10.750 1.4659 0.01411 0.00851 -0.0410 0.1806 1.0000
11.000 1.4841 0.01439 0.00881 -0.0394 0.1788 1.0000
11.250 1.5018 0.01466 0.00911 -0.0377 0.1773 1.0000
11.500 1.5187 0.01497 0.00944 -0.0360 0.1752 1.0000
11.750 1.5347 0.01532 0.00981 -0.0342 0.1731 1.0000
12.000 1.5496 0.01573 0.01024 -0.0323 0.1708 1.0000
12.250 1.5631 0.01621 0.01072 -0.0303 0.1684 1.0000
12.500 1.5765 0.01672 0.01125 -0.0284 0.1662 1.0000
12.750 1.5918 0.01716 0.01174 -0.0269 0.1648 1.0000
13.000 1.6059 0.01769 0.01230 -0.0253 0.1629 1.0000
13.250 1.6185 0.01832 0.01296 -0.0237 0.1608 1.0000
13.500 1.6295 0.01907 0.01373 -0.0221 0.1586 1.0000
13.750 1.6386 0.01998 0.01466 -0.0205 0.1564 1.0000
14.000 1.6470 0.02101 0.01573 -0.0190 0.1541 1.0000
14.250 1.6592 0.02189 0.01665 -0.0179 0.1525 1.0000
14.500 1.6697 0.02292 0.01773 -0.0169 0.1507 1.0000
14.750 1.6785 0.02413 0.01898 -0.0159 0.1485 1.0000
15.000 1.6853 0.02555 0.02044 -0.0150 0.1462 1.0000
15.250 1.6898 0.02722 0.02215 -0.0142 0.1440 1.0000
15.500 1.6948 0.02894 0.02391 -0.0136 0.1419 1.0000
15.750 1.7020 0.03053 0.02556 -0.0131 0.1400 1.0000
16.000 1.7065 0.03238 0.02746 -0.0127 0.1378 1.0000
16.250 1.7086 0.03450 0.02964 -0.0123 0.1356 1.0000
16.500 1.7055 0.03718 0.03235 -0.0121 0.1327 1.0000
16.750 1.7037 0.03978 0.03501 -0.0120 0.1304 1.0000
17.000 1.7044 0.04219 0.03749 -0.0119 0.1286 1.0000
17.250 1.7006 0.04512 0.04047 -0.0120 0.1257 1.0000
17.500 1.6952 0.04830 0.04371 -0.0123 0.1236 1.0000
17.750 1.6832 0.05232 0.04778 -0.0128 0.1208 1.0000
18.000 1.6802 0.05539 0.05092 -0.0133 0.1189 1.0000
18.250 1.6731 0.05901 0.05461 -0.0140 0.1161 1.0000
18.500 1.6617 0.06325 0.05890 -0.0149 0.1134 1.0000
18.750 1.6456 0.06812 0.06384 -0.0162 0.1105 1.0000
19.000 1.6365 0.07227 0.06806 -0.0173 0.1082 1.0000
19.250 1.6227 0.07709 0.07294 -0.0188 0.1051 1.0000
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