EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 855 AIRFOIL (e855-il) Reynolds number: 200,000 Max Cl/Cd: 77.37 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e855-il-200000-n5.txt Download as CSV file: xf-e855-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5560 0.07150 0.06753 -0.0685 1.0000 0.0096
-12.000 -0.5882 0.06362 0.05946 -0.0726 1.0000 0.0094
-11.750 -0.6102 0.05827 0.05399 -0.0748 1.0000 0.0094
-11.500 -0.6342 0.05329 0.04884 -0.0761 1.0000 0.0093
-11.250 -0.6519 0.04976 0.04521 -0.0762 1.0000 0.0094
-11.000 -0.6689 0.04638 0.04170 -0.0763 0.9995 0.0094
-10.750 -0.6608 0.04198 0.03700 -0.0826 0.9934 0.0095
-10.500 -0.6518 0.03859 0.03335 -0.0871 0.9855 0.0096
-10.250 -0.6395 0.03572 0.03022 -0.0898 0.9765 0.0099
-10.000 -0.6227 0.03328 0.02754 -0.0915 0.9679 0.0100
-9.750 -0.6016 0.03102 0.02503 -0.0933 0.9603 0.0105
-9.500 -0.5849 0.02917 0.02297 -0.0934 0.9497 0.0108
-9.250 -0.5655 0.02747 0.02107 -0.0936 0.9397 0.0112
-9.000 -0.5410 0.02589 0.01937 -0.0948 0.9324 0.0119
-8.750 -0.5177 0.02469 0.01806 -0.0953 0.9228 0.0125
-8.500 -0.4911 0.02364 0.01690 -0.0961 0.9142 0.0139
-8.250 -0.4618 0.02233 0.01543 -0.0975 0.9069 0.0152
-8.000 -0.4337 0.02119 0.01421 -0.0987 0.8975 0.0163
-7.750 -0.3987 0.02003 0.01292 -0.1010 0.8907 0.0182
-7.500 -0.3665 0.01895 0.01173 -0.1028 0.8804 0.0205
-7.250 -0.3275 0.01807 0.01074 -0.1059 0.8718 0.0252
-7.000 -0.2876 0.01726 0.00984 -0.1090 0.8618 0.0312
-6.750 -0.2508 0.01651 0.00902 -0.1115 0.8498 0.0394
-6.500 -0.2142 0.01581 0.00825 -0.1139 0.8368 0.0499
-6.250 -0.1801 0.01521 0.00760 -0.1158 0.8232 0.0628
-6.000 -0.1486 0.01469 0.00704 -0.1170 0.8096 0.0790
-5.750 -0.1188 0.01424 0.00654 -0.1179 0.7960 0.1000
-5.500 -0.0908 0.01376 0.00606 -0.1184 0.7826 0.1277
-5.250 -0.0646 0.01325 0.00562 -0.1186 0.7694 0.1674
-5.000 -0.0397 0.01267 0.00521 -0.1187 0.7566 0.2278
-4.750 -0.0149 0.01219 0.00495 -0.1186 0.7449 0.3054
-4.500 0.0115 0.01202 0.00485 -0.1185 0.7338 0.3606
-4.250 0.0386 0.01200 0.00478 -0.1183 0.7229 0.3958
-4.000 0.0653 0.01201 0.00472 -0.1181 0.7120 0.4197
-3.750 0.0925 0.01205 0.00464 -0.1179 0.7022 0.4373
-3.500 0.1197 0.01210 0.00457 -0.1177 0.6929 0.4512
-3.250 0.1467 0.01213 0.00449 -0.1175 0.6835 0.4636
-3.000 0.1738 0.01220 0.00443 -0.1173 0.6749 0.4762
-2.750 0.2004 0.01226 0.00444 -0.1170 0.6660 0.4896
-2.500 0.2273 0.01233 0.00444 -0.1168 0.6584 0.5014
-2.250 0.2544 0.01237 0.00438 -0.1166 0.6504 0.5102
-2.000 0.2814 0.01240 0.00434 -0.1165 0.6432 0.5162
-1.750 0.3085 0.01242 0.00427 -0.1163 0.6356 0.5223
-1.500 0.3357 0.01246 0.00423 -0.1162 0.6292 0.5275
-1.250 0.3626 0.01248 0.00421 -0.1161 0.6223 0.5327
-1.000 0.3900 0.01254 0.00417 -0.1160 0.6162 0.5386
-0.750 0.4168 0.01256 0.00417 -0.1158 0.6098 0.5436
-0.500 0.4438 0.01261 0.00418 -0.1157 0.6036 0.5489
-0.250 0.4712 0.01268 0.00417 -0.1157 0.5985 0.5549
0.000 0.4979 0.01271 0.00422 -0.1155 0.5927 0.5600
0.250 0.5249 0.01277 0.00425 -0.1154 0.5873 0.5658
0.500 0.5522 0.01286 0.00428 -0.1153 0.5822 0.5721
0.750 0.5786 0.01290 0.00436 -0.1151 0.5767 0.5776
1.000 0.6057 0.01298 0.00442 -0.1150 0.5720 0.5841
1.250 0.6328 0.01307 0.00449 -0.1150 0.5677 0.5903
1.500 0.6592 0.01313 0.00460 -0.1148 0.5625 0.5972
1.750 0.6860 0.01323 0.00469 -0.1146 0.5578 0.6044
2.250 0.7394 0.01342 0.00494 -0.1144 0.5492 0.6194
2.500 0.7656 0.01350 0.00508 -0.1141 0.5447 0.6275
2.750 0.7922 0.01362 0.00521 -0.1140 0.5405 0.6363
3.000 0.8187 0.01373 0.00537 -0.1138 0.5366 0.6456
3.250 0.8444 0.01383 0.00556 -0.1135 0.5321 0.6557
3.500 0.8705 0.01394 0.00574 -0.1132 0.5280 0.6669
3.750 0.8969 0.01407 0.00590 -0.1130 0.5244 0.6790
4.000 0.9223 0.01419 0.00612 -0.1127 0.5202 0.6918
4.250 0.9473 0.01430 0.00636 -0.1122 0.5160 0.7065
4.500 0.9725 0.01442 0.00657 -0.1117 0.5120 0.7231
4.750 0.9982 0.01456 0.00676 -0.1114 0.5085 0.7420
5.000 1.0215 0.01466 0.00704 -0.1106 0.5042 0.7630
5.500 1.0676 0.01485 0.00750 -0.1087 0.4957 0.8233
5.750 1.0892 0.01489 0.00771 -0.1073 0.4916 0.8779
6.000 1.1169 0.01494 0.00793 -0.1074 0.4853 1.0000
6.250 1.1415 0.01514 0.00812 -0.1070 0.4795 1.0000
6.500 1.1641 0.01534 0.00839 -0.1062 0.4726 1.0000
6.750 1.1860 0.01552 0.00859 -0.1052 0.4646 1.0000
7.000 1.2063 0.01571 0.00885 -0.1039 0.4555 1.0000
7.250 1.2273 0.01592 0.00904 -0.1028 0.4473 1.0000
7.500 1.2470 0.01613 0.00936 -0.1014 0.4383 1.0000
7.750 1.2666 0.01637 0.00965 -0.1000 0.4300 1.0000
8.000 1.2845 0.01662 0.00996 -0.0983 0.4202 1.0000
8.250 1.3009 0.01687 0.01028 -0.0963 0.4102 1.0000
8.500 1.3161 0.01716 0.01062 -0.0942 0.3998 1.0000
8.750 1.3293 0.01751 0.01099 -0.0917 0.3868 1.0000
9.000 1.3416 0.01791 0.01143 -0.0891 0.3720 1.0000
9.250 1.3524 0.01839 0.01192 -0.0864 0.3541 1.0000
9.500 1.3593 0.01901 0.01251 -0.0831 0.3317 1.0000
9.750 1.3627 0.01984 0.01326 -0.0795 0.3052 1.0000
10.000 1.3614 0.02095 0.01424 -0.0755 0.2757 1.0000
10.250 1.3569 0.02236 0.01551 -0.0714 0.2470 1.0000
10.500 1.3519 0.02396 0.01700 -0.0676 0.2218 1.0000
10.750 1.3469 0.02574 0.01869 -0.0643 0.1998 1.0000
11.000 1.3426 0.02766 0.02057 -0.0614 0.1795 1.0000
11.250 1.3387 0.02971 0.02258 -0.0589 0.1617 1.0000
11.500 1.3351 0.03191 0.02476 -0.0567 0.1462 1.0000
11.750 1.3319 0.03423 0.02705 -0.0549 0.1325 1.0000
12.000 1.3298 0.03659 0.02943 -0.0534 0.1210 1.0000
12.250 1.3273 0.03912 0.03196 -0.0522 0.1100 1.0000
12.500 1.3246 0.04176 0.03461 -0.0511 0.1009 1.0000
12.750 1.3231 0.04440 0.03728 -0.0502 0.0916 1.0000
13.000 1.3223 0.04706 0.03998 -0.0495 0.0840 1.0000
13.500 1.3200 0.05269 0.04569 -0.0486 0.0701 1.0000
13.750 1.3176 0.05578 0.04882 -0.0483 0.0643 1.0000
14.000 1.3183 0.05858 0.05169 -0.0481 0.0587 1.0000
14.500 1.3170 0.06473 0.05795 -0.0482 0.0492 1.0000
14.750 1.3152 0.06806 0.06131 -0.0483 0.0450 1.0000
15.000 1.3152 0.07121 0.06455 -0.0486 0.0415 1.0000
15.250 1.3150 0.07446 0.06786 -0.0489 0.0377 1.0000
15.500 1.3117 0.07818 0.07161 -0.0495 0.0347 1.0000
15.750 1.3134 0.08131 0.07487 -0.0500 0.0318 1.0000
16.000 1.3119 0.08491 0.07853 -0.0507 0.0290 1.0000
16.250 1.3092 0.08874 0.08241 -0.0515 0.0269 1.0000
16.500 1.3098 0.09217 0.08599 -0.0523 0.0246 1.0000
16.750 1.3079 0.09601 0.08989 -0.0533 0.0225 1.0000
17.000 1.3046 0.10012 0.09406 -0.0545 0.0207 1.0000
17.250 1.3040 0.10387 0.09794 -0.0556 0.0192 1.0000
17.500 1.3017 0.10791 0.10208 -0.0569 0.0177 1.0000
17.750 1.2969 0.11244 0.10667 -0.0586 0.0164 1.0000
18.000 1.2956 0.11643 0.11079 -0.0601 0.0152 1.0000
18.250 1.2933 0.12063 0.11511 -0.0617 0.0141 1.0000
18.500 1.2895 0.12512 0.11969 -0.0637 0.0131 1.0000
18.750 1.2835 0.13006 0.12471 -0.0659 0.0124 1.0000
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Polar data table (+)
Polar graphs
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