EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 1210 AIRFOIL (e1210-il) Reynolds number: 50,000 Max Cl/Cd: 25.78 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e1210-il-50000-n5.txt Download as CSV file: xf-e1210-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2051 0.10974 0.10304 -0.0369 1.0000 0.0870
-9.500 -0.2105 0.10653 0.09994 -0.0379 1.0000 0.0877
-9.250 -0.2111 0.10392 0.09748 -0.0379 1.0000 0.0891
-9.000 -0.2085 0.10203 0.09573 -0.0370 1.0000 0.0909
-8.750 -0.2166 0.09993 0.09382 -0.0363 0.9997 0.0914
-8.500 -0.1992 0.09500 0.08890 -0.0425 0.9670 0.0932
-8.250 -0.1881 0.08943 0.08331 -0.0500 0.9392 0.0956
-8.000 -0.1831 0.08268 0.07651 -0.0591 0.9145 0.0969
-7.750 -0.1471 0.08011 0.07387 -0.0625 0.8941 0.1010
-7.500 -0.1371 0.07496 0.06863 -0.0690 0.8714 0.1034
-7.250 -0.1389 0.06828 0.06181 -0.0776 0.8501 0.1054
-7.000 -0.1426 0.06146 0.05477 -0.0850 0.8310 0.1077
-6.750 -0.1233 0.05970 0.05290 -0.0855 0.8128 0.1107
-6.500 -0.1196 0.05504 0.04798 -0.0891 0.7967 0.1139
-6.250 -0.1250 0.04769 0.03991 -0.0947 0.7836 0.1180
-6.000 -0.1022 0.04739 0.03966 -0.0934 0.7672 0.1209
-5.750 -0.0860 0.04514 0.03713 -0.0939 0.7530 0.1249
-5.500 -0.0722 0.04099 0.03220 -0.0959 0.7416 0.1302
-5.250 -0.0504 0.04040 0.03166 -0.0949 0.7269 0.1335
-5.000 -0.0286 0.03896 0.02996 -0.0947 0.7149 0.1379
-4.750 -0.0078 0.03663 0.02697 -0.0952 0.7030 0.1438
-4.500 0.0153 0.03593 0.02627 -0.0945 0.6906 0.1476
-4.250 0.0402 0.03493 0.02504 -0.0941 0.6799 0.1529
-4.000 0.0638 0.03357 0.02318 -0.0941 0.6680 0.1589
-3.750 0.0900 0.03291 0.02248 -0.0936 0.6581 0.1636
-3.500 0.1139 0.03224 0.02165 -0.0931 0.6461 0.1694
-3.250 0.1416 0.03133 0.02034 -0.0929 0.6372 0.1761
-3.000 0.1653 0.03092 0.01995 -0.0923 0.6256 0.1814
-2.750 0.1930 0.03031 0.01907 -0.0919 0.6169 0.1888
-2.500 0.2176 0.02989 0.01853 -0.0914 0.6061 0.1954
-2.250 0.2446 0.02947 0.01802 -0.0909 0.5975 0.2027
-2.000 0.2702 0.02920 0.01752 -0.0904 0.5875 0.2115
-1.750 0.2967 0.02884 0.01718 -0.0899 0.5787 0.2192
-1.500 0.3226 0.02866 0.01683 -0.0893 0.5701 0.2296
-1.250 0.3479 0.02846 0.01664 -0.0886 0.5610 0.2390
-1.000 0.3762 0.02824 0.01622 -0.0883 0.5538 0.2522
-0.750 0.3998 0.02823 0.01630 -0.0876 0.5441 0.2647
-0.500 0.4272 0.02803 0.01603 -0.0871 0.5371 0.2813
-0.250 0.4513 0.02805 0.01612 -0.0864 0.5287 0.3005
0.000 0.4764 0.02797 0.01611 -0.0858 0.5208 0.3263
0.250 0.5039 0.02771 0.01589 -0.0853 0.5150 0.3636
0.500 0.5241 0.02784 0.01637 -0.0843 0.5061 0.4155
0.750 0.5467 0.02752 0.01645 -0.0830 0.4996 0.5115
1.000 0.5646 0.02699 0.01656 -0.0800 0.4941 0.6929
1.250 0.6011 0.02706 0.01690 -0.0812 0.4849 1.0000
1.500 0.6279 0.02738 0.01690 -0.0808 0.4790 1.0000
1.750 0.6513 0.02793 0.01725 -0.0802 0.4726 1.0000
2.000 0.6727 0.02859 0.01779 -0.0794 0.4653 1.0000
2.250 0.6992 0.02893 0.01789 -0.0789 0.4598 1.0000
2.500 0.7219 0.02954 0.01836 -0.0782 0.4538 1.0000
2.750 0.7411 0.03037 0.01914 -0.0773 0.4468 1.0000
3.000 0.7667 0.03078 0.01938 -0.0767 0.4416 1.0000
3.250 0.7925 0.03123 0.01964 -0.0763 0.4369 1.0000
3.500 0.8062 0.03242 0.02089 -0.0749 0.4295 1.0000
3.750 0.8293 0.03301 0.02137 -0.0742 0.4242 1.0000
4.000 0.8578 0.03328 0.02145 -0.0740 0.4203 1.0000
4.250 0.8684 0.03472 0.02297 -0.0724 0.4137 1.0000
4.500 0.8852 0.03572 0.02396 -0.0713 0.4079 1.0000
4.750 0.9110 0.03614 0.02426 -0.0708 0.4037 1.0000
5.000 0.9354 0.03673 0.02473 -0.0703 0.3997 1.0000
5.250 0.9336 0.03897 0.02716 -0.0680 0.3928 1.0000
5.500 0.9508 0.03994 0.02810 -0.0670 0.3880 1.0000
5.750 0.9791 0.04021 0.02825 -0.0667 0.3845 1.0000
6.000 0.9834 0.04210 0.03019 -0.0648 0.3794 1.0000
6.250 0.9674 0.04528 0.03355 -0.0620 0.3728 1.0000
6.500 0.9842 0.04627 0.03451 -0.0610 0.3688 1.0000
6.750 1.0169 0.04624 0.03437 -0.0609 0.3660 1.0000
7.000 0.9019 0.05765 0.04616 -0.0564 0.3534 1.0000
7.250 0.9201 0.05864 0.04712 -0.0557 0.3502 1.0000
7.500 0.9512 0.05835 0.04674 -0.0549 0.3482 1.0000
8.000 0.8790 0.07363 0.06224 -0.0575 0.3308 1.0000
9.000 0.8087 0.09794 0.08676 -0.0636 0.3045 1.0000
9.250 0.8145 0.10101 0.08984 -0.0640 0.3010 1.0000
9.500 0.8300 0.10275 0.09156 -0.0638 0.2985 1.0000
9.750 0.8508 0.10374 0.09252 -0.0632 0.2966 1.0000
10.000 0.8149 0.11254 0.10143 -0.0666 0.2888 1.0000
10.250 0.8196 0.11582 0.10473 -0.0673 0.2854 1.0000
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Polar data table (+)
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