EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 585 AIRFOIL (e585-il) Reynolds number: 200,000 Max Cl/Cd: 78.63 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e585-il-200000-n5.txt Download as CSV file: xf-e585-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 585 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1939 0.11656 0.11292 -0.0758 0.9608 0.0205
-11.250 -0.1831 0.11239 0.10875 -0.0793 0.9538 0.0206
-11.000 -0.1784 0.10506 0.10139 -0.0848 0.9475 0.0144
-10.750 -0.1630 0.10138 0.09770 -0.0881 0.9417 0.0138
-10.500 -0.1520 0.09622 0.09253 -0.0927 0.9349 0.0133
-10.250 -0.1417 0.09035 0.08663 -0.0987 0.9281 0.0141
-10.000 -0.1334 0.08382 0.08008 -0.1052 0.9196 0.0144
-9.750 -0.1193 0.07955 0.07577 -0.1100 0.9113 0.0141
-9.500 -0.1098 0.07418 0.07038 -0.1157 0.9016 0.0138
-9.250 -0.1040 0.06891 0.06507 -0.1209 0.8902 0.0135
-9.000 -0.1052 0.06248 0.05861 -0.1273 0.8779 0.0132
-8.750 -0.1174 0.05575 0.05174 -0.1333 0.8648 0.0132
-8.500 -0.1345 0.05112 0.04695 -0.1346 0.8533 0.0130
-8.250 -0.1505 0.04761 0.04327 -0.1335 0.8429 0.0128
-7.750 -0.1860 0.03522 0.02978 -0.1288 0.8265 0.0113
-7.500 -0.1796 0.03245 0.02666 -0.1273 0.8210 0.0112
-7.250 -0.1697 0.02995 0.02381 -0.1258 0.8152 0.0112
-7.000 -0.1553 0.02756 0.02100 -0.1246 0.8105 0.0111
-6.750 -0.1379 0.02549 0.01854 -0.1236 0.8061 0.0111
-6.500 -0.1188 0.02373 0.01644 -0.1225 0.8012 0.0112
-6.250 -0.0969 0.02220 0.01456 -0.1218 0.7971 0.0113
-6.000 -0.0729 0.02088 0.01298 -0.1213 0.7937 0.0114
-5.750 -0.0505 0.01980 0.01180 -0.1206 0.7894 0.0116
-5.500 -0.0276 0.01892 0.01083 -0.1200 0.7851 0.0120
-5.250 -0.0036 0.01815 0.00996 -0.1195 0.7814 0.0126
-5.000 0.0212 0.01742 0.00910 -0.1192 0.7783 0.0133
-4.750 0.0442 0.01681 0.00840 -0.1185 0.7741 0.0143
-4.500 0.0675 0.01625 0.00780 -0.1180 0.7700 0.0156
-4.250 0.0927 0.01585 0.00731 -0.1177 0.7665 0.0184
-4.000 0.1186 0.01540 0.00679 -0.1176 0.7634 0.0230
-3.750 0.1429 0.01492 0.00633 -0.1172 0.7597 0.0310
-3.500 0.1669 0.01446 0.00597 -0.1168 0.7556 0.0537
-3.250 0.1918 0.01398 0.00567 -0.1167 0.7521 0.1017
-3.000 0.2168 0.01334 0.00540 -0.1169 0.7489 0.1976
-2.750 0.2405 0.01249 0.00515 -0.1171 0.7457 0.3649
-2.500 0.2588 0.01173 0.00537 -0.1155 0.7416 0.6069
-2.250 0.2823 0.01189 0.00564 -0.1142 0.7379 0.6922
-2.000 0.3089 0.01206 0.00573 -0.1136 0.7346 0.7246
-1.750 0.3363 0.01223 0.00579 -0.1133 0.7319 0.7455
-1.500 0.3602 0.01241 0.00593 -0.1123 0.7277 0.7604
-1.250 0.3843 0.01260 0.00607 -0.1113 0.7237 0.7758
-1.000 0.4071 0.01285 0.00628 -0.1097 0.7201 0.7949
-0.750 0.4310 0.01302 0.00639 -0.1084 0.7172 0.8079
-0.500 0.4566 0.01309 0.00640 -0.1081 0.7129 0.8150
-0.250 0.4816 0.01312 0.00640 -0.1076 0.7086 0.8181
0.000 0.5089 0.01313 0.00634 -0.1076 0.7048 0.8212
0.250 0.5383 0.01314 0.00624 -0.1081 0.7018 0.8243
0.500 0.5645 0.01319 0.00627 -0.1081 0.6971 0.8278
0.750 0.5914 0.01321 0.00626 -0.1082 0.6928 0.8304
1.000 0.6186 0.01322 0.00623 -0.1082 0.6890 0.8325
1.250 0.6469 0.01324 0.00620 -0.1084 0.6857 0.8349
1.500 0.6713 0.01331 0.00629 -0.1080 0.6804 0.8376
1.750 0.6985 0.01334 0.00629 -0.1082 0.6758 0.8402
2.000 0.7281 0.01335 0.00625 -0.1087 0.6719 0.8431
2.250 0.7528 0.01341 0.00635 -0.1084 0.6663 0.8457
2.500 0.7782 0.01344 0.00638 -0.1081 0.6609 0.8478
2.750 0.8064 0.01345 0.00635 -0.1083 0.6566 0.8499
3.000 0.8299 0.01353 0.00649 -0.1077 0.6504 0.8528
3.250 0.8562 0.01357 0.00655 -0.1077 0.6448 0.8559
3.500 0.8840 0.01361 0.00658 -0.1079 0.6395 0.8587
3.750 0.9072 0.01368 0.00671 -0.1073 0.6324 0.8612
4.000 0.9339 0.01369 0.00670 -0.1072 0.6267 0.8634
4.250 0.9558 0.01378 0.00688 -0.1063 0.6188 0.8665
4.500 0.9819 0.01382 0.00692 -0.1061 0.6122 0.8697
4.750 1.0048 0.01393 0.00709 -0.1055 0.6039 0.8733
5.000 1.0302 0.01397 0.00714 -0.1052 0.5966 0.8761
5.250 1.0504 0.01408 0.00734 -0.1039 0.5873 0.8793
5.500 1.0732 0.01417 0.00746 -0.1032 0.5786 0.8827
5.750 1.0955 0.01428 0.00761 -0.1023 0.5686 0.8866
6.000 1.1158 0.01442 0.00780 -0.1011 0.5577 0.8908
6.250 1.1349 0.01455 0.00797 -0.0996 0.5465 0.8953
6.500 1.1543 0.01471 0.00816 -0.0983 0.5343 0.9002
6.750 1.1723 0.01491 0.00838 -0.0967 0.5210 0.9053
7.000 1.1861 0.01510 0.00859 -0.0942 0.5067 0.9114
7.250 1.2003 0.01537 0.00888 -0.0919 0.4913 0.9188
7.500 1.2121 0.01566 0.00919 -0.0892 0.4754 0.9287
7.750 1.2241 0.01601 0.00957 -0.0867 0.4584 0.9433
8.000 1.2385 0.01639 0.00996 -0.0849 0.4398 1.0000
8.250 1.2519 0.01703 0.01055 -0.0831 0.4202 1.0000
8.500 1.2639 0.01775 0.01122 -0.0813 0.4011 1.0000
8.750 1.2745 0.01854 0.01198 -0.0793 0.3808 1.0000
9.000 1.2830 0.01947 0.01285 -0.0771 0.3605 1.0000
9.250 1.2905 0.02049 0.01381 -0.0748 0.3410 1.0000
9.500 1.2979 0.02156 0.01485 -0.0727 0.3215 1.0000
9.750 1.3043 0.02275 0.01600 -0.0706 0.3026 1.0000
10.000 1.3093 0.02408 0.01727 -0.0685 0.2838 1.0000
10.250 1.3152 0.02542 0.01860 -0.0666 0.2656 1.0000
10.500 1.3203 0.02687 0.02001 -0.0647 0.2469 1.0000
10.750 1.3251 0.02840 0.02151 -0.0629 0.2295 1.0000
11.000 1.3288 0.03007 0.02313 -0.0612 0.2121 1.0000
11.500 1.3373 0.03349 0.02651 -0.0582 0.1801 1.0000
11.750 1.3414 0.03532 0.02833 -0.0568 0.1645 1.0000
12.000 1.3452 0.03722 0.03022 -0.0555 0.1497 1.0000
12.250 1.3486 0.03920 0.03219 -0.0544 0.1355 1.0000
12.500 1.3523 0.04124 0.03422 -0.0533 0.1227 1.0000
12.750 1.3554 0.04339 0.03637 -0.0523 0.1102 1.0000
13.000 1.3581 0.04564 0.03862 -0.0514 0.0989 1.0000
13.250 1.3603 0.04801 0.04099 -0.0506 0.0882 1.0000
13.500 1.3631 0.05039 0.04339 -0.0500 0.0777 1.0000
13.750 1.3653 0.05288 0.04593 -0.0494 0.0683 1.0000
14.000 1.3670 0.05551 0.04859 -0.0489 0.0600 1.0000
14.250 1.3676 0.05833 0.05143 -0.0485 0.0526 1.0000
14.500 1.3680 0.06125 0.05439 -0.0483 0.0461 1.0000
14.750 1.3691 0.06416 0.05737 -0.0481 0.0404 1.0000
15.000 1.3678 0.06744 0.06070 -0.0481 0.0360 1.0000
15.250 1.3683 0.07058 0.06394 -0.0482 0.0318 1.0000
15.500 1.3660 0.07417 0.06759 -0.0485 0.0285 1.0000
15.750 1.3654 0.07760 0.07113 -0.0489 0.0253 1.0000
16.000 1.3611 0.08162 0.07522 -0.0495 0.0230 1.0000
16.250 1.3602 0.08526 0.07903 -0.0501 0.0207 1.0000
16.500 1.3560 0.08945 0.08330 -0.0510 0.0187 1.0000
16.750 1.3521 0.09369 0.08767 -0.0521 0.0171 1.0000
17.000 1.3485 0.09796 0.09206 -0.0533 0.0154 1.0000
17.250 1.3424 0.10270 0.09690 -0.0548 0.0143 1.0000
17.500 1.3376 0.10733 0.10168 -0.0563 0.0131 1.0000
17.750 1.3327 0.11205 0.10654 -0.0581 0.0121 1.0000
18.000 1.3262 0.11712 0.11173 -0.0601 0.0114 1.0000
18.250 1.3178 0.12260 0.11731 -0.0625 0.0108 1.0000
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Polar data table (+)
Polar graphs
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