EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 580 AIRFOIL (e580-il) Reynolds number: 100,000 Max Cl/Cd: 52.13 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e580-il-100000.txt Download as CSV file: xf-e580-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 580 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3404 0.12018 0.11567 -0.0388 1.0000 0.1221
-9.750 -0.3688 0.11841 0.11404 -0.0395 1.0000 0.1266
-9.500 -0.4115 0.11672 0.11251 -0.0409 1.0000 0.1276
-9.250 -0.3780 0.11337 0.10914 -0.0359 1.0000 0.1311
-9.000 -0.3771 0.11184 0.10765 -0.0333 1.0000 0.1345
-8.750 -0.3903 0.11013 0.10603 -0.0319 1.0000 0.1386
-8.500 -0.4462 0.10836 0.10444 -0.0337 1.0000 0.1425
-8.250 -0.4286 0.10482 0.10091 -0.0321 0.9987 0.1456
-8.000 -0.3999 0.10164 0.09769 -0.0347 0.9942 0.1534
-7.750 -0.3994 0.09654 0.09263 -0.0408 0.9866 0.1621
-7.250 -0.3708 0.08919 0.08528 -0.0479 0.9730 0.1810
-7.000 -0.3893 0.08480 0.08096 -0.0527 0.9612 0.1927
-6.750 -0.3956 0.07999 0.07618 -0.0584 0.9498 0.2074
-6.250 -0.3980 0.04704 0.04071 -0.0921 0.9270 0.0795
-6.000 -0.3593 0.04262 0.03531 -0.0954 0.9215 0.0691
-5.750 -0.3175 0.03922 0.03155 -0.0991 0.9182 0.0671
-5.500 -0.2932 0.03742 0.02943 -0.0992 0.9094 0.0672
-5.250 -0.2509 0.03551 0.02713 -0.1021 0.9052 0.0687
-5.000 -0.2234 0.03410 0.02552 -0.1022 0.8977 0.0688
-4.750 -0.1872 0.03267 0.02392 -0.1034 0.8923 0.0694
-4.500 -0.1455 0.03114 0.02233 -0.1054 0.8891 0.0711
-4.250 -0.1277 0.03032 0.02162 -0.1039 0.8795 0.0732
-4.000 -0.0884 0.02931 0.02071 -0.1057 0.8754 0.0796
-3.750 -0.0643 0.02873 0.02020 -0.1055 0.8670 0.0878
-3.500 -0.0229 0.02759 0.01912 -0.1086 0.8620 0.1093
-3.250 0.0223 0.02686 0.02047 -0.1110 0.8589 0.5705
-3.000 0.0304 0.02818 0.02178 -0.1061 0.8479 0.5971
-2.750 0.0464 0.02988 0.02358 -0.0989 0.8434 0.6329
-2.500 0.0449 0.03122 0.02494 -0.0918 0.8320 0.6582
-2.250 0.0591 0.03220 0.02593 -0.0845 0.8281 0.6892
-2.000 0.0564 0.03294 0.02667 -0.0781 0.8167 0.7056
-1.750 0.0898 0.03266 0.02623 -0.0776 0.8134 0.7208
-1.500 0.0970 0.03294 0.02646 -0.0745 0.8028 0.7267
-1.250 0.1454 0.03227 0.02556 -0.0789 0.7993 0.7342
-1.000 0.1636 0.03230 0.02551 -0.0779 0.7911 0.7385
-0.750 0.1969 0.03192 0.02501 -0.0791 0.7855 0.7432
-0.500 0.2486 0.03110 0.02401 -0.0837 0.7832 0.7481
-0.250 0.2656 0.03147 0.02431 -0.0835 0.7731 0.7520
0.000 0.3059 0.03081 0.02355 -0.0854 0.7694 0.7554
0.250 0.3571 0.02997 0.02259 -0.0893 0.7674 0.7595
0.500 0.3704 0.03055 0.02313 -0.0886 0.7564 0.7629
0.750 0.4236 0.02980 0.02226 -0.0933 0.7536 0.7668
1.000 0.4736 0.02899 0.02138 -0.0967 0.7515 0.7702
1.250 0.4793 0.02968 0.02208 -0.0942 0.7400 0.7733
1.500 0.5344 0.02889 0.02121 -0.0989 0.7374 0.7772
1.750 0.5933 0.02809 0.02031 -0.1045 0.7351 0.7814
2.000 0.5964 0.02882 0.02109 -0.1012 0.7234 0.7843
2.250 0.6466 0.02803 0.02025 -0.1048 0.7205 0.7876
2.500 0.6564 0.02878 0.02104 -0.1029 0.7096 0.7915
2.750 0.7102 0.02807 0.02027 -0.1074 0.7060 0.7959
3.000 0.7239 0.02863 0.02088 -0.1058 0.6963 0.7993
3.250 0.7662 0.02807 0.02031 -0.1080 0.6914 0.8028
3.500 0.8142 0.02748 0.01970 -0.1114 0.6873 0.8073
3.750 0.8300 0.02814 0.02041 -0.1104 0.6767 0.8119
4.000 0.8781 0.02737 0.01964 -0.1133 0.6729 0.8159
4.250 0.8850 0.02818 0.02055 -0.1107 0.6617 0.8200
4.500 0.9380 0.02743 0.01976 -0.1147 0.6574 0.8250
4.750 0.9468 0.02821 0.02065 -0.1123 0.6465 0.8298
5.000 0.9951 0.02746 0.01989 -0.1152 0.6418 0.8350
5.250 1.0060 0.02824 0.02079 -0.1133 0.6308 0.8405
5.500 1.0573 0.02746 0.01998 -0.1168 0.6258 0.8456
5.750 1.0641 0.02822 0.02089 -0.1139 0.6146 0.8516
6.000 1.0987 0.02815 0.02086 -0.1152 0.6068 0.8584
6.250 1.1227 0.02815 0.02094 -0.1145 0.5979 0.8652
6.750 1.1835 0.02796 0.02088 -0.1153 0.5807 0.8803
7.000 1.1970 0.02847 0.02152 -0.1134 0.5700 0.8895
7.250 1.2378 0.02786 0.02091 -0.1151 0.5623 0.9003
7.500 1.2498 0.02815 0.02137 -0.1126 0.5514 0.9133
7.750 1.2666 0.02828 0.02163 -0.1108 0.5413 0.9301
8.000 1.3117 0.02745 0.02079 -0.1131 0.5323 0.9562
8.250 1.3351 0.02786 0.02138 -0.1133 0.5194 1.0000
8.500 1.3635 0.02822 0.02183 -0.1143 0.5067 1.0000
8.750 1.3952 0.02841 0.02208 -0.1155 0.4941 1.0000
9.000 1.4276 0.02849 0.02219 -0.1168 0.4809 1.0000
9.250 1.4581 0.02857 0.02229 -0.1176 0.4673 1.0000
9.500 1.4849 0.02871 0.02244 -0.1177 0.4532 1.0000
9.750 1.5074 0.02894 0.02267 -0.1171 0.4388 1.0000
10.000 1.5252 0.02926 0.02301 -0.1157 0.4240 1.0000
10.250 1.5383 0.02965 0.02342 -0.1135 0.4091 1.0000
10.500 1.5475 0.03018 0.02397 -0.1107 0.3942 1.0000
10.750 1.5537 0.03084 0.02464 -0.1075 0.3789 1.0000
11.000 1.5579 0.03164 0.02545 -0.1043 0.3635 1.0000
11.250 1.5592 0.03261 0.02644 -0.1008 0.3479 1.0000
11.500 1.5585 0.03376 0.02762 -0.0973 0.3322 1.0000
11.750 1.5567 0.03510 0.02898 -0.0939 0.3165 1.0000
12.000 1.5536 0.03664 0.03055 -0.0906 0.3006 1.0000
12.250 1.5499 0.03838 0.03234 -0.0876 0.2848 1.0000
12.500 1.5451 0.04035 0.03431 -0.0849 0.2690 1.0000
12.750 1.5394 0.04254 0.03651 -0.0823 0.2534 1.0000
13.000 1.5330 0.04495 0.03892 -0.0800 0.2380 1.0000
13.250 1.5258 0.04759 0.04156 -0.0780 0.2231 1.0000
13.500 1.5178 0.05047 0.04443 -0.0763 0.2086 1.0000
13.750 1.5093 0.05358 0.04752 -0.0749 0.1946 1.0000
14.000 1.5003 0.05693 0.05086 -0.0738 0.1813 1.0000
14.250 1.4907 0.06051 0.05442 -0.0730 0.1686 1.0000
14.500 1.4813 0.06427 0.05814 -0.0726 0.1565 1.0000
14.750 1.4703 0.06846 0.06241 -0.0725 0.1451 1.0000
15.000 1.4604 0.07277 0.06680 -0.0727 0.1340 1.0000
15.250 1.4520 0.07702 0.07108 -0.0730 0.1238 1.0000
15.500 1.4444 0.08125 0.07528 -0.0734 0.1142 1.0000
15.750 1.4351 0.08590 0.07999 -0.0741 0.1049 1.0000
16.000 1.4253 0.09083 0.08502 -0.0751 0.0955 1.0000
16.250 1.4153 0.09583 0.09003 -0.0763 0.0864 1.0000
16.500 1.4057 0.10079 0.09491 -0.0775 0.0775 1.0000
16.750 1.3949 0.10625 0.10046 -0.0792 0.0693 1.0000
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