EPPLER E854 AIRFOIL (e854-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E854 AIRFOIL (e854-il) Reynolds number: 500,000 Max Cl/Cd: 115.92 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e854-il-500000.txt Download as CSV file: xf-e854-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2937 0.11874 0.11662 -0.0412 1.0000 0.0200
-11.750 -0.2965 0.11461 0.11252 -0.0426 1.0000 0.0206
-8.250 -0.4898 0.02772 0.02335 -0.0943 0.9669 0.0108
-8.000 -0.4628 0.02503 0.02043 -0.0958 0.9622 0.0103
-7.750 -0.4336 0.02170 0.01674 -0.0979 0.9594 0.0100
-7.500 -0.4108 0.01959 0.01438 -0.0977 0.9515 0.0099
-7.250 -0.3793 0.01780 0.01240 -0.0991 0.9478 0.0099
-7.000 -0.3515 0.01637 0.01081 -0.0995 0.9417 0.0100
-6.750 -0.3215 0.01517 0.00949 -0.1003 0.9358 0.0102
-6.500 -0.2854 0.01412 0.00833 -0.1024 0.9324 0.0106
-6.250 -0.2562 0.01270 0.00681 -0.1035 0.9230 0.0121
-6.000 -0.2139 0.01198 0.00600 -0.1068 0.9188 0.0147
-5.750 -0.1758 0.01095 0.00494 -0.1095 0.9093 0.0256
-5.500 -0.1345 0.01034 0.00437 -0.1127 0.8998 0.0446
-5.250 -0.0953 0.00983 0.00391 -0.1155 0.8875 0.0704
-5.000 -0.0613 0.00933 0.00351 -0.1173 0.8722 0.1111
-4.750 -0.0312 0.00879 0.00311 -0.1182 0.8555 0.1748
-4.500 -0.0043 0.00808 0.00274 -0.1188 0.8390 0.2869
-4.250 0.0224 0.00771 0.00259 -0.1189 0.8235 0.3799
-4.000 0.0498 0.00766 0.00252 -0.1188 0.8087 0.4205
-3.750 0.0771 0.00768 0.00246 -0.1187 0.7945 0.4469
-3.500 0.1043 0.00772 0.00243 -0.1185 0.7813 0.4655
-3.250 0.1315 0.00777 0.00238 -0.1183 0.7689 0.4790
-3.000 0.1587 0.00784 0.00235 -0.1181 0.7572 0.4922
-2.750 0.1858 0.00789 0.00232 -0.1179 0.7460 0.5025
-2.500 0.2129 0.00792 0.00229 -0.1177 0.7350 0.5116
-2.250 0.2402 0.00799 0.00226 -0.1176 0.7250 0.5214
-2.000 0.2674 0.00805 0.00227 -0.1174 0.7157 0.5323
-1.750 0.2944 0.00810 0.00229 -0.1172 0.7062 0.5429
-1.500 0.3218 0.00815 0.00228 -0.1172 0.6974 0.5515
-1.250 0.3491 0.00819 0.00227 -0.1171 0.6895 0.5577
-1.000 0.3767 0.00823 0.00226 -0.1170 0.6813 0.5641
-0.750 0.4041 0.00827 0.00226 -0.1169 0.6741 0.5695
-0.500 0.4315 0.00829 0.00227 -0.1169 0.6662 0.5756
-0.250 0.4592 0.00836 0.00227 -0.1169 0.6598 0.5816
0.000 0.4865 0.00836 0.00230 -0.1168 0.6527 0.5875
0.250 0.5143 0.00845 0.00232 -0.1168 0.6464 0.5941
0.500 0.5415 0.00845 0.00237 -0.1168 0.6399 0.6001
0.750 0.5692 0.00852 0.00241 -0.1168 0.6339 0.6072
1.000 0.5967 0.00857 0.00247 -0.1168 0.6282 0.6138
1.250 0.6241 0.00861 0.00253 -0.1167 0.6221 0.6216
1.500 0.6517 0.00869 0.00260 -0.1167 0.6168 0.6289
1.750 0.6791 0.00873 0.00268 -0.1167 0.6111 0.6378
2.000 0.7063 0.00878 0.00277 -0.1166 0.6057 0.6462
2.250 0.7340 0.00887 0.00287 -0.1167 0.6007 0.6556
2.500 0.7611 0.00890 0.00298 -0.1166 0.5951 0.6663
2.750 0.7882 0.00897 0.00308 -0.1165 0.5899 0.6774
3.000 0.8153 0.00904 0.00321 -0.1164 0.5845 0.6895
3.250 0.8417 0.00907 0.00332 -0.1161 0.5780 0.7028
3.500 0.8681 0.00915 0.00344 -0.1159 0.5715 0.7181
3.750 0.8937 0.00916 0.00355 -0.1155 0.5637 0.7356
4.000 0.9191 0.00922 0.00368 -0.1150 0.5556 0.7552
4.250 0.9434 0.00924 0.00379 -0.1143 0.5464 0.7778
4.500 0.9673 0.00924 0.00392 -0.1134 0.5370 0.8059
5.000 1.0093 0.00918 0.00419 -0.1103 0.5209 0.8984
5.250 1.0369 0.00917 0.00427 -0.1102 0.5118 1.0000
5.500 1.0623 0.00932 0.00441 -0.1098 0.5021 1.0000
5.750 1.0874 0.00944 0.00457 -0.1094 0.4906 1.0000
6.000 1.1117 0.00959 0.00475 -0.1088 0.4773 1.0000
6.250 1.1348 0.00979 0.00492 -0.1080 0.4606 1.0000
6.500 1.1572 0.01001 0.00513 -0.1070 0.4403 1.0000
6.750 1.1778 0.01033 0.00537 -0.1057 0.4131 1.0000
7.000 1.1955 0.01079 0.00569 -0.1039 0.3745 1.0000
7.250 1.2067 0.01162 0.00622 -0.1011 0.3123 1.0000
7.500 1.2133 0.01275 0.00697 -0.0976 0.2452 1.0000
7.750 1.2200 0.01377 0.00769 -0.0941 0.1924 1.0000
8.000 1.2276 0.01469 0.00839 -0.0908 0.1526 1.0000
8.250 1.2361 0.01557 0.00910 -0.0877 0.1222 1.0000
8.500 1.2455 0.01640 0.00981 -0.0848 0.0980 1.0000
8.750 1.2554 0.01721 0.01053 -0.0820 0.0791 1.0000
9.000 1.2653 0.01803 0.01128 -0.0794 0.0641 1.0000
9.250 1.2748 0.01888 0.01210 -0.0768 0.0519 1.0000
9.500 1.2843 0.01975 0.01295 -0.0742 0.0424 1.0000
9.750 1.2923 0.02073 0.01391 -0.0716 0.0348 1.0000
10.000 1.3005 0.02173 0.01490 -0.0691 0.0287 1.0000
10.250 1.3092 0.02274 0.01596 -0.0669 0.0238 1.0000
10.500 1.3121 0.02418 0.01739 -0.0641 0.0192 1.0000
10.750 1.3221 0.02522 0.01848 -0.0624 0.0160 1.0000
11.000 1.3244 0.02687 0.02017 -0.0599 0.0128 1.0000
11.250 1.3314 0.02824 0.02156 -0.0582 0.0103 1.0000
11.500 1.3313 0.03027 0.02369 -0.0560 0.0087 1.0000
11.750 1.3367 0.03194 0.02544 -0.0545 0.0077 1.0000
12.000 1.3395 0.03391 0.02750 -0.0530 0.0069 1.0000
12.250 1.3326 0.03688 0.03058 -0.0511 0.0062 1.0000
12.500 1.3361 0.03901 0.03282 -0.0500 0.0059 1.0000
12.750 1.3386 0.04129 0.03521 -0.0491 0.0057 1.0000
13.000 1.3409 0.04367 0.03770 -0.0483 0.0053 1.0000
13.250 1.3432 0.04613 0.04025 -0.0476 0.0050 1.0000
13.500 1.3441 0.04880 0.04301 -0.0471 0.0047 1.0000
13.750 1.3429 0.05181 0.04611 -0.0468 0.0044 1.0000
14.000 1.3390 0.05524 0.04965 -0.0465 0.0043 1.0000
14.250 1.3322 0.05913 0.05367 -0.0464 0.0042 1.0000
14.500 1.3236 0.06342 0.05810 -0.0464 0.0040 1.0000
14.750 1.3233 0.06676 0.06157 -0.0467 0.0039 1.0000
15.000 1.3222 0.07030 0.06524 -0.0471 0.0039 1.0000
15.250 1.3207 0.07401 0.06909 -0.0476 0.0038 1.0000
15.500 1.3176 0.07806 0.07329 -0.0484 0.0036 1.0000
15.750 1.3139 0.08228 0.07765 -0.0493 0.0036 1.0000
16.000 1.3089 0.08680 0.08235 -0.0505 0.0036 1.0000
16.250 1.3033 0.09160 0.08731 -0.0519 0.0035 1.0000
16.500 1.2968 0.09664 0.09251 -0.0536 0.0035 1.0000
16.750 1.2890 0.10204 0.09808 -0.0557 0.0035 1.0000
17.000 1.2804 0.10775 0.10395 -0.0580 0.0035 1.0000
17.250 1.2710 0.11377 0.11015 -0.0607 0.0034 1.0000
17.500 1.2605 0.12016 0.11671 -0.0638 0.0035 1.0000
17.750 1.2491 0.12691 0.12363 -0.0673 0.0034 1.0000
18.000 1.2375 0.13392 0.13081 -0.0712 0.0035 1.0000
18.250 1.2243 0.14149 0.13856 -0.0756 0.0035 1.0000
18.500 1.2109 0.14940 0.14664 -0.0804 0.0035 1.0000
18.750 1.1967 0.15781 0.15520 -0.0857 0.0036 1.0000
19.000 1.1822 0.16657 0.16413 -0.0913 0.0036 1.0000
19.250 1.1669 0.17597 0.17367 -0.0975 0.0037 1.0000
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