EPPLER E854 AIRFOIL (e854-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E854 AIRFOIL (e854-il) Reynolds number: 200,000 Max Cl/Cd: 80.64 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e854-il-200000-n5.txt Download as CSV file: xf-e854-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4359 0.08818 0.08475 -0.0501 1.0000 0.0095
-10.250 -0.4574 0.07942 0.07605 -0.0533 1.0000 0.0092
-10.000 -0.5021 0.06525 0.06182 -0.0609 1.0000 0.0088
-9.750 -0.5330 0.05838 0.05487 -0.0643 1.0000 0.0086
-9.500 -0.5638 0.05374 0.05019 -0.0651 1.0000 0.0085
-9.250 -0.5778 0.04603 0.04209 -0.0751 0.9905 0.0084
-9.000 -0.5725 0.03927 0.03474 -0.0816 0.9807 0.0083
-8.750 -0.5581 0.03478 0.02973 -0.0847 0.9724 0.0084
-8.500 -0.5413 0.03152 0.02603 -0.0859 0.9636 0.0085
-8.250 -0.5172 0.02871 0.02283 -0.0876 0.9575 0.0087
-8.000 -0.4949 0.02653 0.02034 -0.0880 0.9491 0.0089
-7.750 -0.4693 0.02462 0.01816 -0.0888 0.9422 0.0092
-7.500 -0.4425 0.02290 0.01620 -0.0895 0.9353 0.0097
-7.250 -0.4152 0.02145 0.01455 -0.0902 0.9282 0.0102
-7.000 -0.3868 0.01999 0.01294 -0.0911 0.9212 0.0109
-6.750 -0.3571 0.01892 0.01176 -0.0923 0.9139 0.0120
-6.500 -0.3240 0.01807 0.01080 -0.0938 0.9071 0.0142
-6.250 -0.2914 0.01710 0.00976 -0.0955 0.8996 0.0174
-6.000 -0.2553 0.01610 0.00861 -0.0977 0.8926 0.0218
-5.750 -0.2195 0.01529 0.00777 -0.0999 0.8843 0.0308
-5.500 -0.1806 0.01453 0.00698 -0.1027 0.8766 0.0454
-5.250 -0.1453 0.01390 0.00634 -0.1046 0.8660 0.0649
-5.000 -0.1093 0.01328 0.00575 -0.1068 0.8553 0.0934
-4.750 -0.0740 0.01264 0.00520 -0.1089 0.8441 0.1370
-4.500 -0.0411 0.01190 0.00467 -0.1107 0.8322 0.2129
-4.250 -0.0114 0.01119 0.00435 -0.1118 0.8197 0.3311
-4.000 0.0183 0.01099 0.00426 -0.1123 0.8070 0.3987
-3.750 0.0479 0.01096 0.00416 -0.1127 0.7948 0.4348
-3.500 0.0771 0.01097 0.00405 -0.1129 0.7832 0.4591
-3.250 0.1060 0.01100 0.00395 -0.1131 0.7720 0.4772
-3.000 0.1346 0.01103 0.00386 -0.1131 0.7613 0.4925
-2.750 0.1621 0.01107 0.00382 -0.1130 0.7505 0.5081
-2.500 0.1896 0.01112 0.00381 -0.1129 0.7406 0.5245
-2.250 0.2175 0.01118 0.00375 -0.1128 0.7312 0.5371
-2.000 0.2447 0.01119 0.00370 -0.1127 0.7216 0.5451
-1.750 0.2724 0.01122 0.00362 -0.1127 0.7130 0.5520
-1.500 0.2999 0.01124 0.00358 -0.1126 0.7047 0.5582
-1.250 0.3274 0.01127 0.00352 -0.1125 0.6962 0.5651
-0.750 0.3822 0.01133 0.00348 -0.1124 0.6810 0.5773
-0.500 0.4098 0.01138 0.00347 -0.1123 0.6742 0.5832
-0.250 0.4368 0.01141 0.00349 -0.1122 0.6666 0.5896
0.000 0.4644 0.01147 0.00350 -0.1122 0.6603 0.5962
0.250 0.4914 0.01151 0.00355 -0.1121 0.6535 0.6027
0.500 0.5188 0.01158 0.00358 -0.1120 0.6473 0.6099
0.750 0.5458 0.01162 0.00365 -0.1119 0.6410 0.6167
1.000 0.5730 0.01169 0.00372 -0.1118 0.6349 0.6245
1.250 0.6002 0.01176 0.00380 -0.1117 0.6295 0.6320
1.500 0.6270 0.01183 0.00391 -0.1116 0.6233 0.6403
1.750 0.6541 0.01191 0.00400 -0.1115 0.6180 0.6491
2.000 0.6809 0.01198 0.00413 -0.1113 0.6125 0.6580
2.250 0.7076 0.01206 0.00426 -0.1112 0.6068 0.6682
2.500 0.7347 0.01216 0.00440 -0.1111 0.6021 0.6789
2.750 0.7607 0.01223 0.00458 -0.1108 0.5963 0.6901
3.000 0.7871 0.01232 0.00474 -0.1105 0.5910 0.7024
3.250 0.8135 0.01243 0.00492 -0.1103 0.5862 0.7162
3.500 0.8391 0.01251 0.00513 -0.1098 0.5804 0.7314
3.750 0.8648 0.01261 0.00530 -0.1094 0.5752 0.7481
4.000 0.8898 0.01270 0.00553 -0.1089 0.5694 0.7673
4.250 0.9136 0.01276 0.00572 -0.1080 0.5623 0.7897
4.500 0.9370 0.01283 0.00591 -0.1070 0.5547 0.8167
4.750 0.9586 0.01286 0.00605 -0.1056 0.5459 0.8517
5.000 0.9793 0.01281 0.00619 -0.1039 0.5348 0.9128
5.250 1.0069 0.01288 0.00631 -0.1040 0.5213 1.0000
5.500 1.0307 0.01305 0.00650 -0.1032 0.5082 1.0000
5.750 1.0542 0.01323 0.00671 -0.1025 0.4954 1.0000
6.000 1.0774 0.01343 0.00695 -0.1017 0.4821 1.0000
6.250 1.0998 0.01365 0.00722 -0.1007 0.4665 1.0000
6.500 1.1209 0.01390 0.00749 -0.0995 0.4476 1.0000
6.750 1.1406 0.01420 0.00778 -0.0981 0.4242 1.0000
7.000 1.1574 0.01460 0.00810 -0.0961 0.3916 1.0000
7.250 1.1686 0.01524 0.00853 -0.0932 0.3440 1.0000
7.500 1.1738 0.01618 0.00917 -0.0895 0.2874 1.0000
7.750 1.1761 0.01725 0.00998 -0.0854 0.2371 1.0000
8.000 1.1794 0.01836 0.01087 -0.0816 0.1948 1.0000
8.250 1.1842 0.01945 0.01179 -0.0782 0.1612 1.0000
8.500 1.1901 0.02052 0.01274 -0.0751 0.1341 1.0000
8.750 1.1970 0.02158 0.01372 -0.0723 0.1123 1.0000
9.000 1.2034 0.02269 0.01477 -0.0695 0.0952 1.0000
9.250 1.2104 0.02382 0.01587 -0.0670 0.0804 1.0000
9.500 1.2169 0.02502 0.01705 -0.0646 0.0685 1.0000
10.000 1.2301 0.02758 0.01967 -0.0603 0.0499 1.0000
10.250 1.2361 0.02900 0.02114 -0.0583 0.0432 1.0000
10.500 1.2405 0.03062 0.02276 -0.0564 0.0368 1.0000
10.750 1.2468 0.03216 0.02438 -0.0548 0.0318 1.0000
11.000 1.2500 0.03403 0.02626 -0.0532 0.0272 1.0000
11.250 1.2557 0.03577 0.02811 -0.0518 0.0238 1.0000
11.500 1.2594 0.03776 0.03014 -0.0506 0.0205 1.0000
11.750 1.2623 0.03990 0.03237 -0.0494 0.0181 1.0000
12.000 1.2663 0.04201 0.03459 -0.0484 0.0159 1.0000
12.250 1.2676 0.04446 0.03711 -0.0475 0.0142 1.0000
12.500 1.2687 0.04701 0.03976 -0.0467 0.0126 1.0000
12.750 1.2719 0.04940 0.04231 -0.0462 0.0114 1.0000
13.000 1.2748 0.05189 0.04490 -0.0457 0.0102 1.0000
13.250 1.2729 0.05500 0.04809 -0.0454 0.0094 1.0000
13.500 1.2723 0.05807 0.05131 -0.0452 0.0088 1.0000
13.750 1.2719 0.06121 0.05460 -0.0451 0.0083 1.0000
14.000 1.2710 0.06450 0.05804 -0.0451 0.0078 1.0000
14.250 1.2700 0.06789 0.06157 -0.0454 0.0075 1.0000
14.500 1.2686 0.07143 0.06525 -0.0458 0.0071 1.0000
14.750 1.2666 0.07515 0.06910 -0.0464 0.0069 1.0000
15.000 1.2632 0.07918 0.07325 -0.0472 0.0066 1.0000
15.250 1.2588 0.08343 0.07763 -0.0482 0.0064 1.0000
15.500 1.2532 0.08803 0.08237 -0.0494 0.0061 1.0000
15.750 1.2497 0.09240 0.08693 -0.0507 0.0059 1.0000
16.000 1.2458 0.09698 0.09170 -0.0522 0.0057 1.0000
16.250 1.2413 0.10177 0.09667 -0.0540 0.0054 1.0000
16.500 1.2355 0.10689 0.10196 -0.0561 0.0052 1.0000
16.750 1.2292 0.11224 0.10749 -0.0585 0.0051 1.0000
17.000 1.2223 0.11785 0.11327 -0.0612 0.0049 1.0000
17.250 1.2148 0.12371 0.11931 -0.0642 0.0048 1.0000
17.500 1.2065 0.12990 0.12567 -0.0675 0.0047 1.0000
17.750 1.1981 0.13630 0.13221 -0.0712 0.0046 1.0000
18.000 1.1881 0.14320 0.13929 -0.0752 0.0046 1.0000
18.250 1.1772 0.15059 0.14684 -0.0797 0.0046 1.0000
18.500 1.1661 0.15826 0.15467 -0.0845 0.0045 1.0000
18.750 1.1531 0.16677 0.16335 -0.0899 0.0045 1.0000
19.000 1.1365 0.17670 0.17344 -0.0962 0.0046 1.0000
19.250 1.1068 0.19178 0.18875 -0.1054 0.0050 1.0000
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