EPPLER E854 AIRFOIL (e854-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E854 AIRFOIL (e854-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.54 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e854-il-1000000-n5.txt Download as CSV file: xf-e854-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6529 0.07981 0.07791 -0.0523 1.0000 0.0025
-13.000 -0.6955 0.06666 0.06461 -0.0592 1.0000 0.0025
-12.750 -0.7260 0.05763 0.05543 -0.0645 1.0000 0.0025
-12.500 -0.7453 0.04805 0.04561 -0.0743 0.9984 0.0025
-12.250 -0.7540 0.04135 0.03869 -0.0817 0.9964 0.0024
-12.000 -0.7485 0.03690 0.03408 -0.0876 0.9945 0.0025
-11.750 -0.7485 0.03266 0.02964 -0.0922 0.9915 0.0025
-11.500 -0.7437 0.02933 0.02611 -0.0962 0.9869 0.0025
-11.250 -0.7281 0.02617 0.02268 -0.1005 0.9837 0.0025
-11.000 -0.7170 0.02466 0.02104 -0.1000 0.9786 0.0025
-10.750 -0.6990 0.02287 0.01908 -0.1009 0.9742 0.0025
-10.250 -0.6635 0.02019 0.01608 -0.1006 0.9627 0.0026
-10.000 -0.6418 0.01917 0.01495 -0.1007 0.9566 0.0027
-9.750 -0.6213 0.01823 0.01390 -0.1003 0.9482 0.0027
-9.500 -0.5946 0.01722 0.01277 -0.1011 0.9412 0.0028
-9.250 -0.5615 0.01629 0.01172 -0.1031 0.9351 0.0028
-9.000 -0.5227 0.01540 0.01072 -0.1063 0.9294 0.0029
-8.750 -0.4757 0.01440 0.00957 -0.1114 0.9222 0.0029
-8.500 -0.4267 0.01349 0.00851 -0.1168 0.9105 0.0030
-8.000 -0.3621 0.01206 0.00670 -0.1201 0.8653 0.0031
-7.750 -0.3384 0.01163 0.00611 -0.1196 0.8424 0.0032
-7.500 -0.3152 0.01127 0.00559 -0.1190 0.8222 0.0033
-7.250 -0.2917 0.01097 0.00516 -0.1184 0.8046 0.0035
-7.000 -0.2675 0.01068 0.00477 -0.1179 0.7888 0.0038
-6.750 -0.2430 0.01044 0.00442 -0.1174 0.7735 0.0040
-6.500 -0.2180 0.01022 0.00411 -0.1170 0.7596 0.0044
-6.000 -0.1671 0.00977 0.00351 -0.1164 0.7344 0.0069
-5.750 -0.1413 0.00956 0.00324 -0.1161 0.7227 0.0099
-5.500 -0.1153 0.00937 0.00301 -0.1159 0.7116 0.0148
-5.250 -0.0892 0.00919 0.00281 -0.1158 0.7015 0.0204
-5.000 -0.0626 0.00902 0.00262 -0.1157 0.6914 0.0269
-4.750 -0.0362 0.00880 0.00243 -0.1156 0.6818 0.0423
-4.500 -0.0099 0.00857 0.00224 -0.1155 0.6729 0.0640
-4.250 0.0170 0.00837 0.00208 -0.1155 0.6644 0.0859
-4.000 0.0439 0.00818 0.00193 -0.1155 0.6563 0.1096
-3.750 0.0708 0.00797 0.00179 -0.1155 0.6480 0.1439
-3.500 0.0978 0.00773 0.00164 -0.1156 0.6406 0.1849
-3.250 0.1245 0.00740 0.00148 -0.1157 0.6334 0.2498
-3.000 0.1514 0.00706 0.00136 -0.1159 0.6269 0.3248
-2.750 0.1788 0.00693 0.00130 -0.1159 0.6197 0.3623
-2.500 0.2064 0.00684 0.00126 -0.1160 0.6133 0.3960
-2.250 0.2343 0.00682 0.00124 -0.1161 0.6069 0.4135
-1.750 0.2901 0.00680 0.00121 -0.1162 0.5955 0.4412
-1.500 0.3178 0.00681 0.00122 -0.1162 0.5895 0.4564
-1.250 0.3458 0.00681 0.00122 -0.1162 0.5842 0.4703
-1.000 0.3738 0.00683 0.00123 -0.1163 0.5789 0.4798
-0.500 0.4296 0.00689 0.00125 -0.1164 0.5690 0.4914
-0.250 0.4575 0.00691 0.00126 -0.1165 0.5637 0.4961
0.000 0.4852 0.00696 0.00128 -0.1164 0.5591 0.5011
0.250 0.5133 0.00698 0.00131 -0.1165 0.5548 0.5057
0.500 0.5412 0.00701 0.00134 -0.1166 0.5499 0.5104
0.750 0.5687 0.00706 0.00138 -0.1166 0.5452 0.5153
1.000 0.5967 0.00710 0.00142 -0.1166 0.5412 0.5202
1.250 0.6246 0.00713 0.00146 -0.1167 0.5367 0.5250
1.500 0.6520 0.00718 0.00152 -0.1167 0.5320 0.5304
2.000 0.7075 0.00726 0.00164 -0.1167 0.5235 0.5409
2.250 0.7349 0.00732 0.00171 -0.1167 0.5185 0.5468
2.500 0.7622 0.00738 0.00178 -0.1166 0.5128 0.5526
2.750 0.7893 0.00745 0.00186 -0.1166 0.5049 0.5589
3.250 0.8426 0.00763 0.00204 -0.1162 0.4866 0.5720
3.500 0.8691 0.00773 0.00213 -0.1160 0.4745 0.5793
3.750 0.8951 0.00784 0.00224 -0.1157 0.4605 0.5867
4.250 0.9468 0.00811 0.00250 -0.1151 0.4325 0.6033
4.500 0.9719 0.00829 0.00265 -0.1147 0.4160 0.6123
4.750 0.9967 0.00848 0.00282 -0.1142 0.3968 0.6223
5.000 1.0201 0.00877 0.00304 -0.1135 0.3698 0.6323
5.250 1.0417 0.00917 0.00332 -0.1125 0.3326 0.6433
5.500 1.0599 0.00980 0.00373 -0.1109 0.2798 0.6555
5.750 1.0769 0.01048 0.00418 -0.1091 0.2282 0.6688
6.000 1.0951 0.01106 0.00462 -0.1075 0.1880 0.6828
6.250 1.1132 0.01163 0.00505 -0.1059 0.1519 0.6978
6.500 1.1328 0.01205 0.00542 -0.1046 0.1290 0.7156
6.750 1.1514 0.01251 0.00583 -0.1030 0.1065 0.7371
7.000 1.1690 0.01298 0.00627 -0.1014 0.0851 0.7613
7.250 1.1875 0.01336 0.00667 -0.0998 0.0719 0.7903
7.500 1.2038 0.01369 0.00707 -0.0977 0.0603 0.8293
7.750 1.2137 0.01384 0.00745 -0.0942 0.0495 0.9594
8.000 1.2281 0.01439 0.00792 -0.0920 0.0365 1.0000
8.250 1.2425 0.01493 0.00841 -0.0898 0.0272 1.0000
8.500 1.2579 0.01543 0.00888 -0.0878 0.0217 1.0000
8.750 1.2723 0.01597 0.00940 -0.0856 0.0163 1.0000
9.000 1.2869 0.01651 0.00994 -0.0836 0.0130 1.0000
9.250 1.3013 0.01706 0.01051 -0.0816 0.0105 1.0000
9.500 1.3151 0.01765 0.01111 -0.0795 0.0083 1.0000
9.750 1.3282 0.01828 0.01176 -0.0774 0.0068 1.0000
10.000 1.3412 0.01892 0.01243 -0.0754 0.0056 1.0000
10.250 1.3531 0.01965 0.01318 -0.0733 0.0044 1.0000
10.500 1.3649 0.02040 0.01397 -0.0712 0.0037 1.0000
10.750 1.3759 0.02122 0.01483 -0.0692 0.0031 1.0000
11.000 1.3856 0.02215 0.01580 -0.0671 0.0025 1.0000
11.250 1.3957 0.02310 0.01682 -0.0652 0.0021 1.0000
11.500 1.4054 0.02412 0.01789 -0.0634 0.0019 1.0000
11.750 1.4140 0.02526 0.01908 -0.0615 0.0017 1.0000
12.000 1.4218 0.02651 0.02040 -0.0598 0.0015 1.0000
12.250 1.4291 0.02786 0.02181 -0.0581 0.0013 1.0000
12.500 1.4368 0.02924 0.02326 -0.0566 0.0013 1.0000
12.750 1.4447 0.03066 0.02475 -0.0553 0.0012 1.0000
13.000 1.4516 0.03221 0.02636 -0.0541 0.0012 1.0000
13.250 1.4579 0.03388 0.02811 -0.0529 0.0011 1.0000
13.500 1.4638 0.03564 0.02995 -0.0518 0.0010 1.0000
13.750 1.4685 0.03757 0.03196 -0.0508 0.0009 1.0000
14.000 1.4732 0.03957 0.03405 -0.0500 0.0009 1.0000
14.250 1.4776 0.04165 0.03621 -0.0493 0.0009 1.0000
14.500 1.4807 0.04395 0.03859 -0.0486 0.0008 1.0000
14.750 1.4838 0.04631 0.04104 -0.0481 0.0008 1.0000
15.000 1.4850 0.04893 0.04375 -0.0477 0.0007 1.0000
15.250 1.4870 0.05157 0.04648 -0.0475 0.0007 1.0000
15.500 1.4812 0.05524 0.05028 -0.0473 0.0006 1.0000
15.750 1.4838 0.05796 0.05309 -0.0474 0.0006 1.0000
16.000 1.4797 0.06163 0.05688 -0.0476 0.0006 1.0000
16.250 1.4731 0.06579 0.06117 -0.0481 0.0006 1.0000
16.500 1.4707 0.06948 0.06497 -0.0488 0.0006 1.0000
16.750 1.4684 0.07324 0.06883 -0.0495 0.0006 1.0000
17.000 1.4637 0.07748 0.07319 -0.0506 0.0006 1.0000
17.250 1.4594 0.08177 0.07760 -0.0518 0.0006 1.0000
17.500 1.4539 0.08637 0.08231 -0.0532 0.0005 1.0000
17.750 1.4479 0.09116 0.08723 -0.0549 0.0005 1.0000
18.000 1.4405 0.09632 0.09251 -0.0568 0.0005 1.0000
18.250 1.4312 0.10193 0.09825 -0.0591 0.0005 1.0000
18.500 1.4221 0.10763 0.10407 -0.0616 0.0005 1.0000
18.750 1.4110 0.11387 0.11044 -0.0644 0.0005 1.0000
19.000 1.4005 0.12009 0.11680 -0.0675 0.0005 1.0000
19.250 1.3878 0.12694 0.12378 -0.0711 0.0005 1.0000
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Polar data table (+)
Polar graphs
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