EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E1212 AIRFOIL (e1212-il) Reynolds number: 200,000 Max Cl/Cd: 59.59 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1212-il-200000-n5.txt Download as CSV file: xf-e1212-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7259 0.09450 0.08949 -0.0370 1.0000 0.0451
-15.250 -0.7363 0.08934 0.08426 -0.0396 1.0000 0.0470
-15.000 -0.7483 0.08410 0.07902 -0.0424 1.0000 0.0485
-14.750 -0.7634 0.07856 0.07343 -0.0454 1.0000 0.0502
-14.500 -0.7816 0.07286 0.06767 -0.0484 1.0000 0.0517
-14.250 -0.8043 0.06677 0.06152 -0.0518 1.0000 0.0528
-14.000 -0.8324 0.06008 0.05476 -0.0555 1.0000 0.0537
-13.750 -0.8634 0.05308 0.04766 -0.0596 1.0000 0.0544
-13.500 -0.8949 0.04591 0.04036 -0.0640 1.0000 0.0548
-13.250 -0.9230 0.03894 0.03322 -0.0688 1.0000 0.0556
-13.000 -0.9438 0.03367 0.02778 -0.0725 1.0000 0.0567
-12.750 -0.9601 0.03069 0.02467 -0.0723 1.0000 0.0582
-12.500 -0.9714 0.02891 0.02283 -0.0696 1.0000 0.0604
-12.250 -0.9694 0.02756 0.02141 -0.0675 1.0000 0.0637
-12.000 -0.9651 0.02628 0.02009 -0.0655 1.0000 0.0677
-11.750 -0.9565 0.02522 0.01899 -0.0637 1.0000 0.0719
-11.500 -0.9449 0.02430 0.01802 -0.0620 1.0000 0.0770
-11.250 -0.9327 0.02341 0.01713 -0.0603 1.0000 0.0820
-11.000 -0.9186 0.02265 0.01635 -0.0587 1.0000 0.0872
-10.750 -0.9032 0.02199 0.01564 -0.0571 1.0000 0.0929
-10.500 -0.8699 0.02124 0.01486 -0.0589 0.9914 0.1004
-10.250 -0.8364 0.02056 0.01417 -0.0606 0.9756 0.1078
-10.000 -0.8020 0.01997 0.01355 -0.0623 0.9537 0.1153
-9.750 -0.7614 0.01944 0.01294 -0.0650 0.9288 0.1232
-9.500 -0.7162 0.01896 0.01234 -0.0685 0.9030 0.1313
-9.250 -0.6749 0.01860 0.01191 -0.0711 0.8728 0.1379
-9.000 -0.6413 0.01830 0.01139 -0.0721 0.8426 0.1441
-8.750 -0.6132 0.01812 0.01113 -0.0720 0.8156 0.1488
-8.500 -0.5870 0.01793 0.01075 -0.0715 0.7916 0.1540
-8.250 -0.5617 0.01775 0.01044 -0.0708 0.7704 0.1582
-8.000 -0.5364 0.01762 0.01021 -0.0701 0.7511 0.1624
-7.750 -0.5109 0.01746 0.00986 -0.0694 0.7332 0.1669
-7.500 -0.4855 0.01727 0.00954 -0.0688 0.7165 0.1707
-7.250 -0.4598 0.01714 0.00934 -0.0681 0.7005 0.1744
-7.000 -0.4337 0.01701 0.00908 -0.0675 0.6859 0.1784
-6.750 -0.4076 0.01686 0.00873 -0.0669 0.6721 0.1825
-6.500 -0.3815 0.01667 0.00850 -0.0664 0.6580 0.1859
-6.250 -0.3551 0.01655 0.00831 -0.0659 0.6454 0.1893
-6.000 -0.3286 0.01644 0.00807 -0.0653 0.6327 0.1932
-5.750 -0.3017 0.01630 0.00779 -0.0649 0.6206 0.1971
-5.500 -0.2752 0.01614 0.00754 -0.0644 0.6093 0.2003
-5.250 -0.2483 0.01599 0.00737 -0.0639 0.5976 0.2036
-5.000 -0.2215 0.01590 0.00718 -0.0635 0.5870 0.2072
-4.750 -0.1942 0.01578 0.00697 -0.0631 0.5760 0.2110
-4.500 -0.1670 0.01570 0.00673 -0.0626 0.5660 0.2145
-4.250 -0.1401 0.01552 0.00655 -0.0622 0.5555 0.2178
-4.000 -0.1131 0.01542 0.00640 -0.0618 0.5461 0.2211
-3.750 -0.0856 0.01533 0.00625 -0.0614 0.5362 0.2248
-3.500 -0.0584 0.01527 0.00608 -0.0610 0.5272 0.2287
-3.250 -0.0307 0.01519 0.00592 -0.0607 0.5176 0.2321
-3.000 -0.0039 0.01507 0.00577 -0.0603 0.5090 0.2355
-2.750 0.0236 0.01498 0.00568 -0.0599 0.5002 0.2393
-2.500 0.0509 0.01493 0.00556 -0.0595 0.4914 0.2433
-2.250 0.0784 0.01489 0.00545 -0.0592 0.4833 0.2473
-2.000 0.1059 0.01483 0.00535 -0.0589 0.4750 0.2512
-1.750 0.1328 0.01477 0.00527 -0.0584 0.4675 0.2552
-1.500 0.1604 0.01471 0.00521 -0.0581 0.4592 0.2595
-1.250 0.1876 0.01470 0.00514 -0.0577 0.4515 0.2641
-1.000 0.2152 0.01471 0.00508 -0.0574 0.4446 0.2688
-0.750 0.2423 0.01464 0.00505 -0.0571 0.4370 0.2735
-0.500 0.2692 0.01465 0.00502 -0.0566 0.4301 0.2785
-0.250 0.2968 0.01464 0.00501 -0.0563 0.4228 0.2841
0.000 0.3240 0.01465 0.00500 -0.0560 0.4158 0.2900
0.250 0.3507 0.01467 0.00501 -0.0556 0.4097 0.2964
0.500 0.3781 0.01467 0.00504 -0.0553 0.4028 0.3035
0.750 0.4050 0.01471 0.00505 -0.0549 0.3960 0.3105
1.000 0.4317 0.01474 0.00510 -0.0545 0.3902 0.3189
1.250 0.4590 0.01477 0.00516 -0.0541 0.3838 0.3291
1.500 0.4855 0.01480 0.00522 -0.0537 0.3776 0.3403
1.750 0.5119 0.01487 0.00529 -0.0533 0.3720 0.3529
2.000 0.5388 0.01490 0.00540 -0.0529 0.3660 0.3679
2.250 0.5651 0.01495 0.00550 -0.0525 0.3602 0.3852
2.750 0.6174 0.01505 0.00575 -0.0516 0.3494 0.4336
3.000 0.6432 0.01508 0.00589 -0.0511 0.3439 0.4651
3.250 0.6684 0.01514 0.00604 -0.0505 0.3391 0.5023
3.500 0.6934 0.01517 0.00622 -0.0498 0.3345 0.5473
3.750 0.7181 0.01515 0.00643 -0.0490 0.3292 0.6040
4.000 0.7412 0.01512 0.00662 -0.0479 0.3243 0.6746
4.250 0.7628 0.01510 0.00682 -0.0463 0.3201 0.7615
4.500 0.7921 0.01504 0.00707 -0.0460 0.3156 0.8835
4.750 0.8396 0.01523 0.00729 -0.0498 0.3098 1.0000
5.000 0.8637 0.01549 0.00748 -0.0491 0.3054 1.0000
5.250 0.8875 0.01577 0.00768 -0.0484 0.3014 1.0000
5.500 0.9123 0.01601 0.00793 -0.0477 0.2970 1.0000
5.750 0.9366 0.01627 0.00818 -0.0471 0.2927 1.0000
6.000 0.9603 0.01656 0.00843 -0.0463 0.2889 1.0000
6.250 0.9835 0.01689 0.00868 -0.0455 0.2855 1.0000
6.500 1.0076 0.01717 0.00899 -0.0449 0.2817 1.0000
6.750 1.0313 0.01746 0.00930 -0.0441 0.2776 1.0000
7.000 1.0542 0.01778 0.00959 -0.0433 0.2737 1.0000
7.250 1.0764 0.01814 0.00990 -0.0424 0.2702 1.0000
7.500 1.0989 0.01850 0.01025 -0.0416 0.2671 1.0000
7.750 1.1216 0.01884 0.01063 -0.0408 0.2637 1.0000
8.000 1.1436 0.01919 0.01102 -0.0399 0.2602 1.0000
8.250 1.1646 0.01957 0.01139 -0.0389 0.2569 1.0000
8.500 1.1848 0.01999 0.01176 -0.0378 0.2538 1.0000
8.750 1.2052 0.02041 0.01220 -0.0367 0.2508 1.0000
9.000 1.2252 0.02082 0.01267 -0.0356 0.2476 1.0000
9.250 1.2444 0.02125 0.01314 -0.0344 0.2446 1.0000
9.500 1.2623 0.02170 0.01361 -0.0330 0.2419 1.0000
9.750 1.2782 0.02218 0.01407 -0.0313 0.2394 1.0000
10.000 1.2938 0.02272 0.01457 -0.0297 0.2369 1.0000
10.250 1.3088 0.02324 0.01518 -0.0280 0.2343 1.0000
10.500 1.3232 0.02380 0.01582 -0.0263 0.2315 1.0000
10.750 1.3370 0.02440 0.01647 -0.0247 0.2288 1.0000
11.000 1.3504 0.02505 0.01715 -0.0231 0.2264 1.0000
11.250 1.3635 0.02575 0.01786 -0.0216 0.2242 1.0000
11.500 1.3769 0.02650 0.01859 -0.0203 0.2221 1.0000
11.750 1.3885 0.02734 0.01952 -0.0189 0.2199 1.0000
12.000 1.3990 0.02827 0.02056 -0.0176 0.2174 1.0000
12.250 1.4088 0.02927 0.02164 -0.0163 0.2149 1.0000
12.500 1.4186 0.03033 0.02276 -0.0152 0.2127 1.0000
12.750 1.4283 0.03143 0.02389 -0.0142 0.2106 1.0000
13.000 1.4386 0.03254 0.02500 -0.0133 0.2085 1.0000
13.250 1.4490 0.03373 0.02621 -0.0125 0.2065 1.0000
13.500 1.4540 0.03531 0.02794 -0.0117 0.2043 1.0000
13.750 1.4589 0.03697 0.02971 -0.0111 0.2019 1.0000
14.000 1.4635 0.03870 0.03154 -0.0105 0.1996 1.0000
14.250 1.4683 0.04046 0.03337 -0.0101 0.1973 1.0000
14.500 1.4751 0.04209 0.03501 -0.0098 0.1952 1.0000
14.750 1.4857 0.04341 0.03630 -0.0093 0.1932 1.0000
15.000 1.4829 0.04606 0.03912 -0.0094 0.1910 1.0000
15.250 1.4798 0.04883 0.04203 -0.0095 0.1886 1.0000
15.500 1.4776 0.05159 0.04491 -0.0098 0.1863 1.0000
15.750 1.4762 0.05432 0.04773 -0.0101 0.1839 1.0000
16.000 1.4798 0.05655 0.04998 -0.0104 0.1817 1.0000
16.250 1.4903 0.05798 0.05137 -0.0103 0.1796 1.0000
16.500 1.4746 0.06270 0.05631 -0.0116 0.1772 1.0000
16.750 1.4610 0.06736 0.06115 -0.0131 0.1746 1.0000
17.000 1.4507 0.07173 0.06564 -0.0146 0.1719 1.0000
17.250 1.4477 0.07520 0.06917 -0.0157 0.1695 1.0000
17.500 1.4578 0.07682 0.07077 -0.0160 0.1673 1.0000
17.750 1.4367 0.08303 0.07716 -0.0185 0.1646 1.0000
18.000 1.3965 0.09237 0.08674 -0.0226 0.1609 1.0000
18.250 1.3801 0.09830 0.09278 -0.0253 0.1577 1.0000
18.500 1.3915 0.09984 0.09430 -0.0257 0.1555 1.0000
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Polar data table (+)
Polar graphs
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