EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1210 AIRFOIL (e1210-il) Reynolds number: 200,000 Max Cl/Cd: 65.09 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1210-il-200000-n5.txt Download as CSV file: xf-e1210-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1210 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7004 0.04014 0.03568 -0.0791 1.0000 0.0326
-11.250 -0.7034 0.03547 0.03078 -0.0835 0.9945 0.0332
-11.000 -0.6828 0.03228 0.02737 -0.0877 0.9749 0.0344
-10.750 -0.6594 0.02963 0.02442 -0.0908 0.9492 0.0358
-10.500 -0.6218 0.02806 0.02274 -0.0948 0.9268 0.0373
-10.250 -0.5810 0.02615 0.02051 -0.0993 0.9031 0.0398
-10.000 -0.5408 0.02506 0.01930 -0.1028 0.8749 0.0417
-9.500 -0.4823 0.02324 0.01702 -0.1048 0.8200 0.0459
-9.250 -0.4583 0.02256 0.01613 -0.1045 0.7967 0.0481
-9.000 -0.4350 0.02194 0.01530 -0.1040 0.7762 0.0501
-8.750 -0.4110 0.02152 0.01473 -0.1034 0.7575 0.0523
-8.500 -0.3875 0.02094 0.01391 -0.1027 0.7405 0.0548
-8.250 -0.3630 0.02065 0.01354 -0.1021 0.7241 0.0570
-8.000 -0.3386 0.02015 0.01280 -0.1015 0.7091 0.0599
-7.750 -0.3136 0.01990 0.01249 -0.1009 0.6949 0.0621
-7.500 -0.2885 0.01955 0.01197 -0.1003 0.6811 0.0650
-7.250 -0.2631 0.01920 0.01149 -0.0997 0.6680 0.0675
-7.000 -0.2375 0.01896 0.01114 -0.0992 0.6558 0.0700
-6.750 -0.2117 0.01855 0.01053 -0.0986 0.6434 0.0730
-6.500 -0.1858 0.01835 0.01028 -0.0981 0.6320 0.0752
-6.250 -0.1596 0.01809 0.00989 -0.0976 0.6204 0.0782
-6.000 -0.1333 0.01777 0.00943 -0.0971 0.6098 0.0810
-5.750 -0.1069 0.01759 0.00918 -0.0966 0.5989 0.0835
-5.500 -0.0802 0.01734 0.00880 -0.0961 0.5889 0.0868
-5.250 -0.0537 0.01709 0.00845 -0.0957 0.5787 0.0896
-5.000 -0.0268 0.01692 0.00823 -0.0952 0.5691 0.0925
-4.750 0.0001 0.01672 0.00789 -0.0948 0.5595 0.0960
-4.500 0.0269 0.01650 0.00761 -0.0943 0.5508 0.0989
-4.250 0.0539 0.01635 0.00741 -0.0939 0.5413 0.1020
-4.000 0.0810 0.01620 0.00712 -0.0934 0.5329 0.1057
-3.750 0.1081 0.01600 0.00689 -0.0930 0.5241 0.1089
-3.500 0.1349 0.01589 0.00671 -0.0926 0.5161 0.1124
-3.250 0.1624 0.01575 0.00650 -0.0922 0.5078 0.1164
-3.000 0.1893 0.01560 0.00630 -0.0918 0.4995 0.1201
-2.750 0.2164 0.01549 0.00616 -0.0914 0.4921 0.1240
-2.500 0.2439 0.01539 0.00599 -0.0910 0.4844 0.1285
-2.250 0.2706 0.01529 0.00583 -0.0906 0.4773 0.1326
-2.000 0.2980 0.01519 0.00573 -0.0902 0.4698 0.1372
-1.750 0.3252 0.01513 0.00560 -0.0898 0.4623 0.1422
-1.500 0.3520 0.01506 0.00549 -0.0894 0.4559 0.1472
-1.250 0.3794 0.01499 0.00543 -0.0890 0.4491 0.1529
-1.000 0.4065 0.01497 0.00535 -0.0886 0.4423 0.1590
-0.750 0.4333 0.01492 0.00530 -0.0882 0.4361 0.1657
-0.500 0.4606 0.01489 0.00526 -0.0879 0.4292 0.1735
-0.250 0.4874 0.01486 0.00524 -0.0875 0.4230 0.1819
0.000 0.5143 0.01489 0.00522 -0.0871 0.4175 0.1923
0.250 0.5414 0.01485 0.00525 -0.0867 0.4112 0.2052
0.500 0.5681 0.01485 0.00526 -0.0863 0.4051 0.2210
0.750 0.5946 0.01487 0.00530 -0.0859 0.3998 0.2423
1.000 0.6215 0.01484 0.00537 -0.0856 0.3940 0.2713
1.250 0.6479 0.01481 0.00545 -0.0852 0.3885 0.3122
1.500 0.6735 0.01478 0.00554 -0.0847 0.3834 0.3691
1.750 0.6993 0.01467 0.00569 -0.0843 0.3782 0.4483
2.000 0.7238 0.01450 0.00585 -0.0835 0.3728 0.5553
2.250 0.7456 0.01428 0.00601 -0.0820 0.3682 0.6935
2.500 0.7822 0.01397 0.00611 -0.0829 0.3633 1.0000
2.750 0.8085 0.01415 0.00625 -0.0825 0.3582 1.0000
3.000 0.8344 0.01436 0.00637 -0.0820 0.3532 1.0000
3.250 0.8598 0.01460 0.00650 -0.0814 0.3489 1.0000
3.500 0.8856 0.01483 0.00667 -0.0809 0.3450 1.0000
3.750 0.9115 0.01505 0.00686 -0.0805 0.3405 1.0000
4.000 0.9369 0.01528 0.00704 -0.0800 0.3360 1.0000
4.250 0.9618 0.01555 0.00721 -0.0794 0.3320 1.0000
4.500 0.9868 0.01582 0.00742 -0.0788 0.3282 1.0000
4.750 1.0123 0.01606 0.00767 -0.0783 0.3242 1.0000
5.000 1.0372 0.01633 0.00791 -0.0777 0.3203 1.0000
5.250 1.0616 0.01661 0.00814 -0.0771 0.3166 1.0000
5.500 1.0855 0.01694 0.00839 -0.0764 0.3133 1.0000
5.750 1.1101 0.01722 0.00868 -0.0758 0.3095 1.0000
6.000 1.1343 0.01751 0.00897 -0.0752 0.3057 1.0000
6.250 1.1579 0.01782 0.00927 -0.0745 0.3021 1.0000
6.500 1.1811 0.01816 0.00957 -0.0738 0.2990 1.0000
6.750 1.2039 0.01854 0.00988 -0.0730 0.2962 1.0000
7.000 1.2272 0.01886 0.01026 -0.0723 0.2930 1.0000
7.250 1.2497 0.01920 0.01063 -0.0715 0.2895 1.0000
7.500 1.2716 0.01955 0.01098 -0.0706 0.2861 1.0000
7.750 1.2929 0.01994 0.01135 -0.0696 0.2831 1.0000
8.000 1.3138 0.02037 0.01172 -0.0687 0.2804 1.0000
8.250 1.3348 0.02077 0.01217 -0.0677 0.2777 1.0000
8.500 1.3552 0.02118 0.01265 -0.0666 0.2748 1.0000
8.750 1.3746 0.02160 0.01311 -0.0655 0.2719 1.0000
9.000 1.3924 0.02203 0.01355 -0.0641 0.2690 1.0000
9.250 1.4090 0.02249 0.01400 -0.0625 0.2665 1.0000
9.500 1.4256 0.02301 0.01448 -0.0610 0.2639 1.0000
9.750 1.4412 0.02352 0.01509 -0.0594 0.2614 1.0000
10.000 1.4566 0.02407 0.01571 -0.0578 0.2588 1.0000
10.250 1.4713 0.02465 0.01635 -0.0562 0.2564 1.0000
10.500 1.4853 0.02527 0.01701 -0.0546 0.2539 1.0000
10.750 1.4990 0.02592 0.01767 -0.0531 0.2516 1.0000
11.000 1.5132 0.02662 0.01834 -0.0517 0.2494 1.0000
11.250 1.5253 0.02741 0.01922 -0.0502 0.2470 1.0000
11.500 1.5362 0.02829 0.02020 -0.0488 0.2446 1.0000
11.750 1.5469 0.02922 0.02122 -0.0474 0.2423 1.0000
12.000 1.5572 0.03021 0.02228 -0.0461 0.2400 1.0000
12.250 1.5672 0.03124 0.02335 -0.0449 0.2378 1.0000
12.500 1.5782 0.03227 0.02439 -0.0439 0.2357 1.0000
12.750 1.5901 0.03331 0.02542 -0.0429 0.2336 1.0000
13.000 1.5953 0.03480 0.02708 -0.0419 0.2314 1.0000
13.250 1.6008 0.03636 0.02876 -0.0410 0.2291 1.0000
13.500 1.6058 0.03800 0.03049 -0.0402 0.2267 1.0000
13.750 1.6112 0.03966 0.03223 -0.0395 0.2244 1.0000
14.000 1.6183 0.04121 0.03382 -0.0389 0.2222 1.0000
14.250 1.6280 0.04257 0.03518 -0.0384 0.2202 1.0000
14.500 1.6302 0.04468 0.03740 -0.0379 0.2181 1.0000
14.750 1.6270 0.04737 0.04025 -0.0377 0.2156 1.0000
15.000 1.6247 0.05006 0.04307 -0.0376 0.2130 1.0000
15.250 1.6237 0.05269 0.04579 -0.0377 0.2105 1.0000
15.500 1.6271 0.05487 0.04802 -0.0376 0.2082 1.0000
15.750 1.6361 0.05646 0.04960 -0.0375 0.2061 1.0000
16.000 1.6266 0.06031 0.05362 -0.0381 0.2036 1.0000
16.250 1.6126 0.06490 0.05839 -0.0391 0.2007 1.0000
16.500 1.6027 0.06910 0.06272 -0.0401 0.1979 1.0000
16.750 1.5997 0.07248 0.06617 -0.0409 0.1953 1.0000
17.000 1.6089 0.07423 0.06791 -0.0411 0.1932 1.0000
17.250 1.5961 0.07910 0.07292 -0.0426 0.1905 1.0000
17.500 1.5585 0.08785 0.08193 -0.0458 0.1867 1.0000
17.750 1.5406 0.09388 0.08809 -0.0481 0.1835 1.0000
18.000 1.5471 0.09616 0.09038 -0.0488 0.1811 1.0000
18.250 1.5691 0.09600 0.09017 -0.0483 0.1793 1.0000
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