EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E853 AIRFOIL (e853-il) Reynolds number: 200,000 Max Cl/Cd: 82.5 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e853-il-200000-n5.txt Download as CSV file: xf-e853-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E853 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4227 0.08768 0.08422 -0.0477 1.0000 0.0075
-9.500 -0.4320 0.08257 0.07918 -0.0492 1.0000 0.0075
-9.250 -0.4418 0.07766 0.07434 -0.0507 1.0000 0.0073
-9.000 -0.4593 0.07064 0.06740 -0.0532 1.0000 0.0073
-8.750 -0.4804 0.06379 0.06058 -0.0560 1.0000 0.0071
-8.500 -0.4906 0.05572 0.05239 -0.0662 0.9935 0.0069
-8.250 -0.4874 0.04673 0.04301 -0.0790 0.9806 0.0068
-8.000 -0.4786 0.03980 0.03557 -0.0851 0.9698 0.0067
-7.500 -0.4473 0.03019 0.02486 -0.0896 0.9496 0.0067
-7.250 -0.4202 0.02667 0.02080 -0.0916 0.9445 0.0068
-7.000 -0.3960 0.02413 0.01784 -0.0921 0.9361 0.0070
-6.750 -0.3648 0.02191 0.01526 -0.0936 0.9317 0.0074
-6.500 -0.3366 0.02027 0.01336 -0.0943 0.9243 0.0078
-6.250 -0.3044 0.01849 0.01140 -0.0960 0.9193 0.0089
-6.000 -0.2714 0.01778 0.01061 -0.0977 0.9130 0.0110
-5.750 -0.2374 0.01687 0.00950 -0.0994 0.9068 0.0131
-5.500 -0.2045 0.01547 0.00797 -0.1011 0.9002 0.0163
-5.250 -0.1704 0.01460 0.00699 -0.1028 0.8931 0.0243
-5.000 -0.1368 0.01384 0.00620 -0.1045 0.8855 0.0396
-4.750 -0.1026 0.01318 0.00556 -0.1063 0.8779 0.0639
-4.500 -0.0708 0.01254 0.00501 -0.1076 0.8692 0.1029
-4.250 -0.0381 0.01183 0.00445 -0.1093 0.8615 0.1701
-4.000 -0.0088 0.01101 0.00404 -0.1105 0.8523 0.2918
-3.750 0.0206 0.01059 0.00395 -0.1112 0.8436 0.4067
-3.500 0.0512 0.01052 0.00385 -0.1118 0.8357 0.4551
-3.250 0.0799 0.01051 0.00376 -0.1119 0.8271 0.4798
-3.000 0.1096 0.01050 0.00363 -0.1123 0.8195 0.4989
-2.750 0.1378 0.01051 0.00358 -0.1123 0.8114 0.5176
-2.500 0.1664 0.01055 0.00355 -0.1124 0.8042 0.5388
-2.250 0.1946 0.01057 0.00350 -0.1125 0.7969 0.5535
-2.000 0.2226 0.01057 0.00344 -0.1125 0.7901 0.5623
-1.750 0.2508 0.01057 0.00336 -0.1126 0.7833 0.5700
-1.500 0.2790 0.01058 0.00331 -0.1127 0.7772 0.5772
-1.250 0.3069 0.01058 0.00327 -0.1127 0.7707 0.5841
-1.000 0.3352 0.01060 0.00322 -0.1129 0.7651 0.5911
-0.750 0.3627 0.01062 0.00323 -0.1128 0.7587 0.5981
-0.500 0.3909 0.01064 0.00322 -0.1129 0.7536 0.6054
-0.250 0.4184 0.01067 0.00325 -0.1129 0.7477 0.6126
0.000 0.4461 0.01070 0.00327 -0.1130 0.7422 0.6204
0.250 0.4741 0.01074 0.00331 -0.1130 0.7374 0.6279
0.500 0.5013 0.01078 0.00338 -0.1130 0.7316 0.6365
0.750 0.5290 0.01082 0.00345 -0.1130 0.7267 0.6446
1.000 0.5565 0.01088 0.00354 -0.1130 0.7218 0.6536
1.250 0.5836 0.01093 0.00364 -0.1129 0.7164 0.6632
1.500 0.6114 0.01098 0.00373 -0.1129 0.7119 0.6730
1.750 0.6381 0.01104 0.00390 -0.1127 0.7066 0.6837
2.000 0.6651 0.01110 0.00404 -0.1126 0.7013 0.6953
2.250 0.6926 0.01117 0.00416 -0.1126 0.6968 0.7078
2.500 0.7183 0.01123 0.00434 -0.1122 0.6904 0.7214
2.750 0.7450 0.01128 0.00450 -0.1119 0.6844 0.7360
3.000 0.7700 0.01132 0.00467 -0.1113 0.6762 0.7521
3.250 0.7955 0.01136 0.00480 -0.1107 0.6681 0.7705
3.500 0.8195 0.01138 0.00492 -0.1097 0.6573 0.7913
3.750 0.8423 0.01138 0.00506 -0.1085 0.6439 0.8154
4.250 0.8833 0.01131 0.00522 -0.1049 0.6110 0.8891
4.500 0.9100 0.01127 0.00530 -0.1045 0.5937 1.0000
4.750 0.9345 0.01142 0.00546 -0.1038 0.5741 1.0000
5.000 0.9578 0.01161 0.00564 -0.1029 0.5473 1.0000
5.250 0.9789 0.01188 0.00587 -0.1016 0.5074 1.0000
5.500 0.9943 0.01243 0.00613 -0.0992 0.4380 1.0000
5.750 1.0014 0.01354 0.00669 -0.0956 0.3409 1.0000
6.000 1.0089 0.01479 0.00747 -0.0925 0.2551 1.0000
6.250 1.0188 0.01596 0.00826 -0.0898 0.1863 1.0000
6.500 1.0316 0.01695 0.00902 -0.0876 0.1390 1.0000
6.750 1.0454 0.01786 0.00977 -0.0855 0.1057 1.0000
7.000 1.0588 0.01875 0.01054 -0.0834 0.0796 1.0000
7.250 1.0717 0.01959 0.01136 -0.0811 0.0607 1.0000
7.500 1.0838 0.02049 0.01220 -0.0788 0.0459 1.0000
7.750 1.0965 0.02139 0.01308 -0.0766 0.0353 1.0000
8.000 1.1091 0.02231 0.01402 -0.0744 0.0266 1.0000
8.250 1.1206 0.02333 0.01509 -0.0721 0.0203 1.0000
8.500 1.1294 0.02459 0.01634 -0.0696 0.0152 1.0000
8.750 1.1402 0.02573 0.01763 -0.0674 0.0126 1.0000
9.000 1.1508 0.02693 0.01888 -0.0654 0.0102 1.0000
9.250 1.1585 0.02841 0.02046 -0.0631 0.0083 1.0000
9.500 1.1687 0.02972 0.02190 -0.0612 0.0074 1.0000
9.750 1.1772 0.03124 0.02356 -0.0592 0.0068 1.0000
10.000 1.1858 0.03282 0.02526 -0.0574 0.0063 1.0000
10.250 1.1934 0.03455 0.02717 -0.0556 0.0058 1.0000
10.500 1.1999 0.03649 0.02925 -0.0539 0.0056 1.0000
10.750 1.2036 0.03895 0.03187 -0.0520 0.0052 1.0000
11.000 1.2083 0.04158 0.03468 -0.0503 0.0051 1.0000
11.250 1.2152 0.04388 0.03721 -0.0489 0.0050 1.0000
11.500 1.2204 0.04647 0.04003 -0.0475 0.0049 1.0000
11.750 1.2234 0.04931 0.04313 -0.0462 0.0048 1.0000
12.000 1.2236 0.05247 0.04656 -0.0450 0.0047 1.0000
12.250 1.2209 0.05598 0.05034 -0.0440 0.0047 1.0000
12.500 1.2153 0.05982 0.05446 -0.0433 0.0046 1.0000
12.750 1.2070 0.06404 0.05895 -0.0429 0.0046 1.0000
13.000 1.1960 0.06872 0.06391 -0.0430 0.0046 1.0000
13.250 1.1831 0.07381 0.06925 -0.0437 0.0046 1.0000
13.500 1.1682 0.07945 0.07514 -0.0450 0.0046 1.0000
13.750 1.1518 0.08566 0.08159 -0.0471 0.0046 1.0000
14.000 1.1346 0.09246 0.08861 -0.0500 0.0046 1.0000
14.250 1.1164 0.10002 0.09639 -0.0538 0.0046 1.0000
14.500 1.0983 0.10826 0.10481 -0.0585 0.0047 1.0000
14.750 1.0795 0.11758 0.11432 -0.0642 0.0047 1.0000
15.000 1.0607 0.12795 0.12485 -0.0710 0.0048 1.0000
15.250 1.0414 0.13972 0.13675 -0.0785 0.0048 1.0000
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Polar data table (+)
Polar graphs
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