EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 855 AIRFOIL (e855-il) Reynolds number: 100,000 Max Cl/Cd: 52.93 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e855-il-100000-n5.txt Download as CSV file: xf-e855-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 855 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4009 0.09611 0.09125 -0.0563 1.0000 0.0220
-11.000 -0.4487 0.08120 0.07634 -0.0636 1.0000 0.0209
-10.750 -0.5148 0.06766 0.06261 -0.0716 1.0000 0.0199
-10.500 -0.5567 0.06103 0.05577 -0.0739 1.0000 0.0194
-10.250 -0.5865 0.05735 0.05198 -0.0734 1.0000 0.0193
-10.000 -0.6149 0.05505 0.04959 -0.0710 1.0000 0.0190
-9.750 -0.6248 0.05114 0.04543 -0.0739 0.9938 0.0192
-9.500 -0.6102 0.04712 0.04113 -0.0786 0.9848 0.0196
-9.250 -0.5937 0.04366 0.03739 -0.0817 0.9750 0.0200
-9.000 -0.5754 0.04065 0.03408 -0.0838 0.9651 0.0207
-8.750 -0.5549 0.03787 0.03095 -0.0855 0.9557 0.0213
-8.500 -0.5296 0.03519 0.02793 -0.0872 0.9479 0.0225
-8.250 -0.5072 0.03299 0.02535 -0.0877 0.9378 0.0241
-8.000 -0.4816 0.03133 0.02365 -0.0889 0.9290 0.0261
-7.750 -0.4520 0.02978 0.02192 -0.0904 0.9215 0.0289
-7.500 -0.4267 0.02813 0.02006 -0.0906 0.9120 0.0315
-7.250 -0.3950 0.02675 0.01865 -0.0925 0.9058 0.0361
-7.000 -0.3700 0.02544 0.01725 -0.0927 0.8955 0.0409
-6.750 -0.3368 0.02428 0.01595 -0.0943 0.8888 0.0488
-6.500 -0.3088 0.02314 0.01482 -0.0952 0.8788 0.0578
-6.250 -0.2776 0.02207 0.01369 -0.0966 0.8700 0.0701
-6.000 -0.2432 0.02102 0.01261 -0.0986 0.8620 0.0873
-5.750 -0.2123 0.02004 0.01166 -0.1000 0.8518 0.1099
-5.500 -0.1764 0.01895 0.01065 -0.1024 0.8439 0.1468
-5.250 -0.1467 0.01790 0.00980 -0.1038 0.8330 0.2048
-5.000 -0.1166 0.01699 0.00931 -0.1051 0.8224 0.3033
-4.750 -0.0812 0.01675 0.00918 -0.1066 0.8133 0.3808
-4.500 -0.0497 0.01676 0.00907 -0.1072 0.8021 0.4207
-4.250 -0.0181 0.01681 0.00895 -0.1078 0.7913 0.4485
-4.000 0.0152 0.01686 0.00883 -0.1086 0.7815 0.4694
-3.750 0.0457 0.01692 0.00872 -0.1090 0.7709 0.4865
-3.500 0.0750 0.01699 0.00866 -0.1091 0.7604 0.5026
-3.250 0.1062 0.01708 0.00860 -0.1095 0.7514 0.5187
-3.000 0.1342 0.01715 0.00857 -0.1094 0.7412 0.5322
-2.750 0.1629 0.01716 0.00843 -0.1095 0.7318 0.5432
-2.500 0.1929 0.01715 0.00827 -0.1099 0.7234 0.5519
-2.250 0.2200 0.01713 0.00814 -0.1098 0.7141 0.5591
-2.000 0.2502 0.01711 0.00797 -0.1102 0.7066 0.5660
-1.750 0.2767 0.01710 0.00786 -0.1101 0.6975 0.5731
-1.500 0.3058 0.01710 0.00775 -0.1103 0.6905 0.5792
-1.250 0.3326 0.01711 0.00767 -0.1102 0.6822 0.5865
-1.000 0.3616 0.01712 0.00759 -0.1104 0.6758 0.5922
-0.750 0.3873 0.01716 0.00758 -0.1101 0.6677 0.5991
-0.500 0.4163 0.01719 0.00751 -0.1104 0.6617 0.6057
-0.250 0.4419 0.01725 0.00756 -0.1101 0.6545 0.6123
0.000 0.4700 0.01730 0.00754 -0.1102 0.6483 0.6197
0.250 0.4966 0.01737 0.00759 -0.1100 0.6422 0.6262
0.500 0.5233 0.01746 0.00764 -0.1100 0.6357 0.6343
0.750 0.5515 0.01753 0.00767 -0.1100 0.6307 0.6412
1.000 0.5766 0.01765 0.00780 -0.1097 0.6244 0.6498
1.250 0.6029 0.01774 0.00792 -0.1095 0.6188 0.6572
1.500 0.6310 0.01785 0.00798 -0.1096 0.6140 0.6663
1.750 0.6547 0.01799 0.00819 -0.1089 0.6080 0.6751
2.000 0.6814 0.01811 0.00833 -0.1088 0.6030 0.6846
2.250 0.7094 0.01825 0.00846 -0.1089 0.5987 0.6955
2.500 0.7324 0.01842 0.00873 -0.1081 0.5928 0.7061
2.750 0.7586 0.01856 0.00891 -0.1079 0.5880 0.7180
3.000 0.7868 0.01869 0.00906 -0.1080 0.5842 0.7312
3.250 0.8083 0.01891 0.00942 -0.1070 0.5787 0.7457
3.500 0.8326 0.01906 0.00966 -0.1064 0.5738 0.7622
3.750 0.8591 0.01918 0.00984 -0.1061 0.5699 0.7811
4.000 0.8800 0.01938 0.01020 -0.1048 0.5651 0.8042
4.250 0.9007 0.01953 0.01051 -0.1034 0.5603 0.8333
4.500 0.9248 0.01959 0.01072 -0.1026 0.5562 0.8762
4.750 0.9586 0.01971 0.01096 -0.1040 0.5518 1.0000
5.000 0.9817 0.02011 0.01143 -0.1036 0.5465 1.0000
5.250 1.0086 0.02043 0.01177 -0.1038 0.5421 1.0000
5.500 1.0386 0.02070 0.01201 -0.1044 0.5384 1.0000
5.750 1.0573 0.02119 0.01264 -0.1032 0.5326 1.0000
6.000 1.0818 0.02154 0.01306 -0.1029 0.5277 1.0000
6.250 1.1114 0.02178 0.01331 -0.1033 0.5236 1.0000
6.500 1.1282 0.02228 0.01396 -0.1017 0.5172 1.0000
6.750 1.1525 0.02257 0.01431 -0.1012 0.5114 1.0000
7.000 1.1759 0.02287 0.01469 -0.1006 0.5053 1.0000
7.250 1.1943 0.02324 0.01518 -0.0992 0.4980 1.0000
7.500 1.2188 0.02340 0.01539 -0.0986 0.4909 1.0000
7.750 1.2346 0.02370 0.01580 -0.0966 0.4817 1.0000
8.000 1.2521 0.02394 0.01615 -0.0949 0.4726 1.0000
8.250 1.2729 0.02405 0.01631 -0.0936 0.4635 1.0000
8.500 1.2832 0.02449 0.01691 -0.0908 0.4537 1.0000
8.750 1.2992 0.02474 0.01724 -0.0888 0.4443 1.0000
9.000 1.3106 0.02503 0.01764 -0.0861 0.4342 1.0000
9.250 1.3168 0.02554 0.01830 -0.0827 0.4234 1.0000
9.500 1.3250 0.02600 0.01887 -0.0797 0.4119 1.0000
9.750 1.3324 0.02651 0.01947 -0.0766 0.3993 1.0000
10.000 1.3375 0.02716 0.02021 -0.0734 0.3855 1.0000
10.250 1.3398 0.02800 0.02114 -0.0701 0.3702 1.0000
10.500 1.3400 0.02906 0.02227 -0.0668 0.3526 1.0000
10.750 1.3390 0.03030 0.02354 -0.0636 0.3329 1.0000
11.000 1.3355 0.03185 0.02509 -0.0606 0.3104 1.0000
11.250 1.3293 0.03376 0.02692 -0.0577 0.2862 1.0000
11.500 1.3207 0.03611 0.02918 -0.0551 0.2616 1.0000
11.750 1.3100 0.03887 0.03184 -0.0528 0.2393 1.0000
12.000 1.2988 0.04195 0.03485 -0.0510 0.2184 1.0000
12.250 1.2877 0.04525 0.03807 -0.0496 0.2003 1.0000
12.500 1.2777 0.04866 0.04144 -0.0485 0.1840 1.0000
12.750 1.2689 0.05212 0.04488 -0.0478 0.1685 1.0000
13.000 1.2611 0.05563 0.04837 -0.0472 0.1548 1.0000
13.500 1.2490 0.06261 0.05535 -0.0467 0.1310 1.0000
13.750 1.2451 0.06602 0.05879 -0.0467 0.1204 1.0000
14.000 1.2414 0.06949 0.06228 -0.0468 0.1111 1.0000
14.250 1.2372 0.07309 0.06587 -0.0470 0.1028 1.0000
14.500 1.2365 0.07636 0.06922 -0.0472 0.0945 1.0000
14.750 1.2333 0.07998 0.07287 -0.0476 0.0876 1.0000
15.000 1.2328 0.08336 0.07634 -0.0481 0.0805 1.0000
15.250 1.2307 0.08696 0.07995 -0.0486 0.0746 1.0000
15.500 1.2301 0.09047 0.08356 -0.0493 0.0686 1.0000
15.750 1.2278 0.09420 0.08728 -0.0500 0.0640 1.0000
16.000 1.2285 0.09764 0.09087 -0.0508 0.0586 1.0000
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Polar data table (+)
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