EPPLER E854 AIRFOIL (e854-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E854 AIRFOIL (e854-il) Reynolds number: 500,000 Max Cl/Cd: 103.88 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e854-il-500000-n5.txt Download as CSV file: xf-e854-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E854 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5796 0.06705 0.06465 -0.0584 1.0000 0.0044
-11.250 -0.6168 0.05698 0.05442 -0.0645 1.0000 0.0042
-11.000 -0.6349 0.05178 0.04913 -0.0671 1.0000 0.0042
-10.750 -0.6450 0.04344 0.04048 -0.0776 0.9961 0.0042
-10.500 -0.6490 0.03750 0.03423 -0.0855 0.9903 0.0042
-10.250 -0.6412 0.03298 0.02935 -0.0916 0.9838 0.0042
-10.000 -0.6319 0.02998 0.02605 -0.0930 0.9763 0.0043
-9.750 -0.6127 0.02713 0.02288 -0.0953 0.9716 0.0043
-9.500 -0.6003 0.02498 0.02047 -0.0948 0.9627 0.0043
-9.250 -0.5807 0.02308 0.01833 -0.0952 0.9558 0.0044
-9.000 -0.5598 0.02153 0.01658 -0.0953 0.9479 0.0044
-8.750 -0.5382 0.02007 0.01493 -0.0953 0.9399 0.0044
-8.500 -0.5106 0.01871 0.01338 -0.0964 0.9340 0.0045
-8.250 -0.4822 0.01756 0.01207 -0.0974 0.9268 0.0046
-8.000 -0.4486 0.01643 0.01079 -0.0995 0.9206 0.0047
-7.750 -0.4123 0.01545 0.00968 -0.1020 0.9137 0.0048
-7.500 -0.3699 0.01436 0.00845 -0.1060 0.9065 0.0050
-7.250 -0.3273 0.01347 0.00743 -0.1099 0.8967 0.0054
-7.000 -0.2867 0.01282 0.00664 -0.1131 0.8841 0.0061
-6.750 -0.2509 0.01232 0.00599 -0.1152 0.8678 0.0069
-6.500 -0.2199 0.01188 0.00540 -0.1162 0.8500 0.0080
-6.250 -0.1919 0.01154 0.00494 -0.1165 0.8328 0.0105
-6.000 -0.1656 0.01122 0.00455 -0.1164 0.8166 0.0144
-5.750 -0.1398 0.01096 0.00420 -0.1163 0.8009 0.0206
-5.500 -0.1142 0.01068 0.00390 -0.1160 0.7863 0.0305
-5.250 -0.0888 0.01041 0.00362 -0.1158 0.7728 0.0442
-5.000 -0.0631 0.01017 0.00337 -0.1156 0.7601 0.0621
-4.750 -0.0374 0.00992 0.00313 -0.1154 0.7477 0.0820
-4.500 -0.0114 0.00968 0.00289 -0.1153 0.7360 0.1064
-4.250 0.0145 0.00939 0.00267 -0.1152 0.7253 0.1435
-4.000 0.0403 0.00905 0.00244 -0.1151 0.7152 0.1942
-3.750 0.0658 0.00861 0.00221 -0.1151 0.7049 0.2729
-3.500 0.0918 0.00825 0.00206 -0.1151 0.6955 0.3532
-3.250 0.1187 0.00816 0.00200 -0.1150 0.6869 0.3906
-3.000 0.1459 0.00812 0.00195 -0.1150 0.6781 0.4189
-2.750 0.1733 0.00811 0.00191 -0.1149 0.6699 0.4369
-2.500 0.2006 0.00812 0.00187 -0.1148 0.6617 0.4505
-2.250 0.2282 0.00813 0.00184 -0.1148 0.6543 0.4632
-2.000 0.2556 0.00816 0.00183 -0.1147 0.6471 0.4777
-1.750 0.2831 0.00818 0.00183 -0.1147 0.6401 0.4924
-1.500 0.3105 0.00820 0.00183 -0.1146 0.6329 0.5022
-1.250 0.3382 0.00823 0.00182 -0.1146 0.6266 0.5085
-1.000 0.3657 0.00825 0.00181 -0.1145 0.6204 0.5140
-0.750 0.3933 0.00830 0.00181 -0.1145 0.6145 0.5195
-0.500 0.4209 0.00832 0.00182 -0.1145 0.6082 0.5245
0.000 0.4761 0.00841 0.00185 -0.1145 0.5972 0.5352
0.250 0.5036 0.00844 0.00188 -0.1144 0.5916 0.5403
0.500 0.5310 0.00849 0.00192 -0.1144 0.5865 0.5460
0.750 0.5587 0.00853 0.00196 -0.1144 0.5811 0.5514
1.000 0.5860 0.00858 0.00202 -0.1143 0.5761 0.5572
1.250 0.6135 0.00864 0.00207 -0.1143 0.5714 0.5633
1.500 0.6410 0.00868 0.00215 -0.1143 0.5663 0.5691
1.750 0.6682 0.00874 0.00222 -0.1142 0.5615 0.5761
2.000 0.6955 0.00880 0.00230 -0.1142 0.5570 0.5825
2.250 0.7230 0.00885 0.00240 -0.1142 0.5521 0.5896
2.500 0.7500 0.00892 0.00249 -0.1141 0.5473 0.5970
2.750 0.7771 0.00899 0.00260 -0.1140 0.5428 0.6053
3.000 0.8043 0.00905 0.00271 -0.1139 0.5376 0.6132
3.250 0.8308 0.00914 0.00283 -0.1137 0.5314 0.6223
3.500 0.8573 0.00920 0.00295 -0.1135 0.5240 0.6320
3.750 0.8830 0.00930 0.00307 -0.1131 0.5154 0.6423
4.250 0.9341 0.00948 0.00334 -0.1123 0.4927 0.6651
4.500 0.9589 0.00959 0.00349 -0.1118 0.4791 0.6784
4.750 0.9837 0.00971 0.00366 -0.1113 0.4667 0.6928
5.000 1.0083 0.00984 0.00384 -0.1107 0.4542 0.7083
5.250 1.0323 0.00999 0.00404 -0.1100 0.4388 0.7253
5.500 1.0554 0.01016 0.00425 -0.1092 0.4211 0.7453
6.000 1.0957 0.01075 0.00482 -0.1064 0.3628 0.7969
6.250 1.1085 0.01138 0.00528 -0.1037 0.3072 0.8322
6.500 1.1161 0.01198 0.00579 -0.0999 0.2569 0.8983
6.750 1.1315 0.01272 0.00634 -0.0979 0.2080 1.0000
7.000 1.1456 0.01349 0.00690 -0.0957 0.1689 1.0000
7.250 1.1595 0.01414 0.00742 -0.0934 0.1403 1.0000
7.500 1.1728 0.01479 0.00796 -0.0911 0.1161 1.0000
7.750 1.1853 0.01548 0.00854 -0.0886 0.0949 1.0000
8.000 1.1995 0.01608 0.00909 -0.0864 0.0796 1.0000
8.250 1.2132 0.01669 0.00967 -0.0842 0.0672 1.0000
8.500 1.2266 0.01734 0.01027 -0.0820 0.0562 1.0000
8.750 1.2388 0.01804 0.01094 -0.0797 0.0458 1.0000
9.000 1.2509 0.01876 0.01163 -0.0775 0.0372 1.0000
9.250 1.2629 0.01949 0.01236 -0.0753 0.0306 1.0000
9.500 1.2739 0.02029 0.01318 -0.0730 0.0251 1.0000
9.750 1.2844 0.02114 0.01404 -0.0708 0.0209 1.0000
10.000 1.2952 0.02201 0.01493 -0.0688 0.0175 1.0000
10.250 1.3035 0.02305 0.01598 -0.0666 0.0139 1.0000
10.500 1.3138 0.02402 0.01701 -0.0647 0.0119 1.0000
10.750 1.3211 0.02522 0.01822 -0.0626 0.0094 1.0000
11.000 1.3299 0.02639 0.01946 -0.0608 0.0079 1.0000
11.250 1.3360 0.02780 0.02089 -0.0590 0.0061 1.0000
11.500 1.3442 0.02914 0.02231 -0.0575 0.0053 1.0000
11.750 1.3509 0.03064 0.02389 -0.0560 0.0045 1.0000
12.000 1.3561 0.03234 0.02566 -0.0545 0.0040 1.0000
12.250 1.3629 0.03397 0.02738 -0.0533 0.0036 1.0000
12.500 1.3686 0.03576 0.02926 -0.0521 0.0033 1.0000
12.750 1.3740 0.03763 0.03122 -0.0511 0.0031 1.0000
13.000 1.3784 0.03965 0.03333 -0.0502 0.0028 1.0000
13.250 1.3807 0.04197 0.03574 -0.0493 0.0026 1.0000
13.500 1.3834 0.04431 0.03818 -0.0486 0.0024 1.0000
13.750 1.3867 0.04665 0.04063 -0.0481 0.0023 1.0000
14.000 1.3891 0.04917 0.04326 -0.0476 0.0022 1.0000
14.250 1.3914 0.05177 0.04597 -0.0473 0.0021 1.0000
14.500 1.3929 0.05453 0.04884 -0.0471 0.0020 1.0000
14.750 1.3936 0.05748 0.05192 -0.0471 0.0019 1.0000
15.000 1.3933 0.06062 0.05518 -0.0472 0.0018 1.0000
15.250 1.3936 0.06380 0.05847 -0.0475 0.0018 1.0000
15.500 1.3923 0.06726 0.06204 -0.0479 0.0016 1.0000
15.750 1.3903 0.07091 0.06582 -0.0485 0.0016 1.0000
16.000 1.3871 0.07485 0.06988 -0.0493 0.0016 1.0000
16.250 1.3827 0.07910 0.07425 -0.0504 0.0015 1.0000
16.500 1.3777 0.08355 0.07884 -0.0516 0.0015 1.0000
16.750 1.3705 0.08847 0.08389 -0.0532 0.0015 1.0000
17.000 1.3608 0.09396 0.08954 -0.0551 0.0014 1.0000
17.250 1.3507 0.09970 0.09542 -0.0573 0.0014 1.0000
17.500 1.3401 0.10568 0.10155 -0.0599 0.0014 1.0000
17.750 1.3302 0.11170 0.10770 -0.0625 0.0013 1.0000
18.000 1.3207 0.11780 0.11394 -0.0655 0.0013 1.0000
18.250 1.3103 0.12420 0.12049 -0.0687 0.0013 1.0000
18.500 1.2998 0.13078 0.12721 -0.0722 0.0013 1.0000
18.750 1.2889 0.13758 0.13416 -0.0760 0.0013 1.0000
19.000 1.2779 0.14455 0.14127 -0.0800 0.0013 1.0000
19.250 1.2662 0.15186 0.14872 -0.0844 0.0013 1.0000
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Polar data table (+)
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