EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 855 AIRFOIL (e855-il) Reynolds number: 100,000 Max Cl/Cd: 47.02 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e855-il-100000.txt Download as CSV file: xf-e855-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3751 0.10575 0.10141 -0.0486 1.0000 0.1299
-9.500 -0.3835 0.08391 0.08018 -0.0503 1.0000 0.0736
-9.250 -0.3717 0.08715 0.08349 -0.0435 1.0000 0.0753
-9.000 -0.3917 0.08159 0.07799 -0.0438 0.9996 0.0676
-8.750 -0.5135 0.06171 0.05783 -0.0617 0.9905 0.0611
-8.500 -0.5028 0.05513 0.05113 -0.0661 0.9840 0.0578
-8.250 -0.5964 0.06411 0.05971 -0.0600 0.9936 0.0585
-8.000 -0.5812 0.05680 0.05206 -0.0665 0.9843 0.0553
-7.750 -0.5730 0.04712 0.04101 -0.0731 0.9727 0.0497
-7.500 -0.5462 0.04289 0.03618 -0.0759 0.9633 0.0494
-7.250 -0.5170 0.03889 0.03187 -0.0785 0.9553 0.0510
-7.000 -0.4788 0.03659 0.02935 -0.0818 0.9485 0.0551
-6.750 -0.4469 0.03425 0.02643 -0.0832 0.9388 0.0594
-6.500 -0.4059 0.03143 0.02352 -0.0865 0.9341 0.0662
-6.250 -0.3759 0.02956 0.02146 -0.0871 0.9240 0.0750
-6.000 -0.3372 0.02779 0.01966 -0.0895 0.9176 0.0894
-5.750 -0.3040 0.02629 0.01825 -0.0909 0.9088 0.1078
-5.500 -0.2695 0.02475 0.01685 -0.0925 0.9011 0.1344
-5.250 -0.2345 0.02309 0.01548 -0.0945 0.8935 0.1794
-5.000 -0.2038 0.02101 0.01439 -0.0965 0.8857 0.3131
-4.750 -0.1657 0.02126 0.01488 -0.0976 0.8782 0.4422
-4.500 -0.1311 0.02178 0.01530 -0.0978 0.8698 0.4834
-4.250 -0.0909 0.02213 0.01556 -0.0989 0.8634 0.5144
-4.000 -0.0504 0.02233 0.01560 -0.1003 0.8572 0.5408
-3.750 -0.0162 0.02251 0.01573 -0.1005 0.8489 0.5591
-3.500 0.0305 0.02243 0.01555 -0.1028 0.8450 0.5784
-3.250 0.0545 0.02258 0.01562 -0.1015 0.8337 0.5934
-3.000 0.0923 0.02253 0.01549 -0.1025 0.8273 0.6103
-2.750 0.1211 0.02252 0.01537 -0.1022 0.8180 0.6243
-2.500 0.1529 0.02237 0.01510 -0.1028 0.8097 0.6371
-2.250 0.1873 0.02215 0.01473 -0.1040 0.8019 0.6487
-2.000 0.2128 0.02211 0.01463 -0.1034 0.7928 0.6566
-1.750 0.2493 0.02181 0.01416 -0.1052 0.7858 0.6666
-1.500 0.2717 0.02185 0.01416 -0.1042 0.7765 0.6738
-1.250 0.3081 0.02159 0.01373 -0.1060 0.7699 0.6829
-1.000 0.3284 0.02171 0.01383 -0.1048 0.7608 0.6902
-0.750 0.3632 0.02152 0.01351 -0.1063 0.7546 0.6988
-0.500 0.3831 0.02168 0.01366 -0.1051 0.7459 0.7065
-0.250 0.4158 0.02156 0.01344 -0.1061 0.7397 0.7148
0.000 0.4368 0.02176 0.01363 -0.1052 0.7320 0.7231
0.250 0.4649 0.02177 0.01359 -0.1054 0.7256 0.7315
0.500 0.4917 0.02189 0.01366 -0.1055 0.7193 0.7409
0.750 0.5127 0.02207 0.01387 -0.1044 0.7120 0.7493
1.000 0.5475 0.02200 0.01371 -0.1058 0.7074 0.7597
1.250 0.5597 0.02248 0.01429 -0.1035 0.6995 0.7692
1.500 0.5881 0.02252 0.01432 -0.1036 0.6943 0.7799
1.750 0.6098 0.02281 0.01464 -0.1028 0.6882 0.7917
2.000 0.6296 0.02314 0.01501 -0.1018 0.6817 0.8047
2.250 0.6594 0.02315 0.01502 -0.1020 0.6776 0.8185
2.500 0.6695 0.02377 0.01577 -0.0994 0.6705 0.8339
2.750 0.6920 0.02394 0.01599 -0.0985 0.6651 0.8516
3.000 0.7214 0.02386 0.01594 -0.0984 0.6615 0.8726
3.250 0.7206 0.02478 0.01707 -0.0941 0.6538 0.9020
3.500 0.7601 0.02480 0.01719 -0.0964 0.6491 0.9447
3.750 0.8211 0.02471 0.01705 -0.1033 0.6456 1.0000
4.000 0.8256 0.02630 0.01873 -0.1020 0.6370 1.0000
4.250 0.8641 0.02650 0.01886 -0.1044 0.6329 1.0000
4.500 0.8833 0.02747 0.01983 -0.1040 0.6271 1.0000
4.750 0.8958 0.02865 0.02106 -0.1026 0.6203 1.0000
5.000 0.9352 0.02866 0.02104 -0.1045 0.6168 1.0000
5.250 0.9297 0.03067 0.02314 -0.1006 0.6085 1.0000
5.500 0.9564 0.03117 0.02367 -0.1008 0.6035 1.0000
5.750 1.0037 0.03074 0.02325 -0.1034 0.6005 1.0000
6.000 0.9761 0.03379 0.02642 -0.0968 0.5899 1.0000
6.250 1.0238 0.03317 0.02583 -0.0993 0.5865 1.0000
6.500 0.9956 0.03638 0.02913 -0.0929 0.5760 1.0000
6.750 1.0455 0.03549 0.02831 -0.0953 0.5721 1.0000
7.000 1.1121 0.03386 0.02671 -0.0999 0.5694 1.0000
7.250 1.0692 0.03759 0.03056 -0.0915 0.5574 1.0000
7.500 1.0578 0.03979 0.03282 -0.0870 0.5485 1.0000
7.750 1.1087 0.03847 0.03163 -0.0891 0.5427 1.0000
8.000 1.2255 0.03359 0.02677 -0.0989 0.5385 1.0000
8.250 1.2019 0.03591 0.02925 -0.0922 0.5275 1.0000
8.500 1.2381 0.03512 0.02856 -0.0925 0.5189 1.0000
8.750 1.2958 0.03313 0.02662 -0.0955 0.5099 1.0000
9.000 1.2994 0.03385 0.02748 -0.0918 0.4994 1.0000
9.250 1.3413 0.03256 0.02629 -0.0928 0.4891 1.0000
9.500 1.3883 0.03096 0.02469 -0.0944 0.4772 1.0000
9.750 1.3983 0.03091 0.02479 -0.0912 0.4646 1.0000
10.000 1.4083 0.03077 0.02478 -0.0879 0.4515 1.0000
10.250 1.4173 0.03052 0.02462 -0.0843 0.4378 1.0000
10.500 1.4229 0.03033 0.02453 -0.0802 0.4232 1.0000
10.750 1.4255 0.03032 0.02460 -0.0760 0.4072 1.0000
11.000 1.4269 0.03041 0.02472 -0.0717 0.3891 1.0000
11.250 1.4175 0.03131 0.02570 -0.0668 0.3697 1.0000
11.500 1.4077 0.03249 0.02691 -0.0623 0.3467 1.0000
11.750 1.3950 0.03423 0.02861 -0.0583 0.3207 1.0000
12.000 1.3805 0.03649 0.03073 -0.0547 0.2918 1.0000
12.250 1.3650 0.03927 0.03330 -0.0517 0.2636 1.0000
12.500 1.3497 0.04242 0.03621 -0.0492 0.2380 1.0000
12.750 1.3355 0.04578 0.03936 -0.0473 0.2153 1.0000
13.000 1.3243 0.04913 0.04253 -0.0457 0.1951 1.0000
13.250 1.3153 0.05244 0.04573 -0.0445 0.1768 1.0000
13.500 1.3093 0.05559 0.04874 -0.0434 0.1606 1.0000
13.750 1.3061 0.05856 0.05161 -0.0426 0.1461 1.0000
14.000 1.3042 0.06151 0.05451 -0.0418 0.1327 1.0000
14.250 1.3041 0.06437 0.05732 -0.0412 0.1206 1.0000
14.500 1.3058 0.06712 0.06003 -0.0406 0.1098 1.0000
14.750 1.3102 0.06962 0.06244 -0.0399 0.0998 1.0000
15.000 1.3102 0.07265 0.06551 -0.0398 0.0916 1.0000
15.250 1.3133 0.07555 0.06851 -0.0394 0.0839 1.0000
15.500 1.3223 0.07772 0.07053 -0.0388 0.0759 1.0000
15.750 1.3175 0.08160 0.07469 -0.0392 0.0709 1.0000
16.000 1.3278 0.08378 0.07673 -0.0386 0.0641 1.0000
16.250 1.3213 0.08799 0.08126 -0.0392 0.0606 1.0000
16.500 1.3211 0.09129 0.08461 -0.0397 0.0564 1.0000
16.750 1.3247 0.09463 0.08805 -0.0397 0.0523 1.0000
17.000 1.3159 0.09938 0.09310 -0.0409 0.0498 1.0000
17.250 1.3100 0.10372 0.09763 -0.0421 0.0474 1.0000
17.500 1.3204 0.10616 0.09992 -0.0420 0.0435 1.0000
17.750 1.3036 0.11211 0.10621 -0.0443 0.0427 1.0000
18.000 1.2875 0.11833 0.11274 -0.0470 0.0421 1.0000
18.250 1.2704 0.12498 0.11967 -0.0501 0.0416 1.0000
18.500 1.2505 0.13235 0.12732 -0.0540 0.0413 1.0000
18.750 1.2286 0.14043 0.13565 -0.0586 0.0414 1.0000
19.000 1.2043 0.14941 0.14486 -0.0641 0.0418 1.0000
19.250 1.1787 0.15926 0.15490 -0.0704 0.0425 1.0000
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Polar data table (+)
Polar graphs
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