EPPLER 59 AIRFOIL (e59-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 59 AIRFOIL (e59-il) Reynolds number: 200,000 Max Cl/Cd: 99.6 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e59-il-200000-n5.txt Download as CSV file: xf-e59-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 59 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2575 0.10942 0.10606 -0.0399 0.9885 0.0215
-9.250 -0.2522 0.10623 0.10288 -0.0424 0.9873 0.0217
-9.000 -0.2492 0.10322 0.09988 -0.0439 0.9848 0.0218
-8.750 -0.2439 0.09982 0.09650 -0.0458 0.9827 0.0219
-8.500 -0.2363 0.09613 0.09279 -0.0477 0.9808 0.0219
-8.250 -0.2280 0.09220 0.08886 -0.0498 0.9793 0.0219
-8.000 -0.2225 0.08868 0.08536 -0.0511 0.9767 0.0219
-7.750 -0.2176 0.08516 0.08185 -0.0522 0.9735 0.0220
-7.500 -0.2105 0.08126 0.07796 -0.0540 0.9710 0.0220
-7.250 -0.2022 0.07722 0.07392 -0.0562 0.9690 0.0220
-7.000 -0.2021 0.07420 0.07093 -0.0560 0.9640 0.0220
-6.750 -0.1972 0.07046 0.06720 -0.0572 0.9602 0.0219
-6.500 -0.1868 0.06537 0.06211 -0.0558 0.9592 0.0189
-6.250 -0.1776 0.06104 0.05779 -0.0589 0.9563 0.0173
-6.000 -0.2466 0.07799 0.07456 -0.0572 0.9615 0.0187
-5.750 -0.2239 0.07309 0.06965 -0.0640 0.9583 0.0165
-5.500 -0.2026 0.06728 0.06383 -0.0720 0.9531 0.0148
-5.250 -0.1658 0.05930 0.05577 -0.0849 0.9483 0.0137
-5.000 -0.1247 0.05314 0.04952 -0.0960 0.9460 0.0139
-4.750 -0.0911 0.05090 0.04722 -0.1012 0.9445 0.0160
-4.250 0.0438 0.03205 0.02751 -0.1348 0.9438 0.0167
-4.000 0.1128 0.02301 0.01727 -0.1477 0.9452 0.0193
-3.750 0.1579 0.02010 0.01355 -0.1520 0.9452 0.0220
-3.500 0.1967 0.01861 0.01178 -0.1549 0.9446 0.0253
-3.250 0.2317 0.01797 0.01087 -0.1565 0.9432 0.0309
-3.000 0.2591 0.01714 0.00985 -0.1567 0.9397 0.0347
-2.750 0.2885 0.01692 0.00957 -0.1572 0.9367 0.0405
-2.500 0.3216 0.01635 0.00886 -0.1584 0.9347 0.0452
-2.250 0.3558 0.01586 0.00833 -0.1598 0.9330 0.0504
-2.000 0.3906 0.01546 0.00784 -0.1613 0.9315 0.0549
-1.750 0.4258 0.01509 0.00742 -0.1630 0.9303 0.0588
-1.500 0.4512 0.01490 0.00723 -0.1626 0.9255 0.0657
-1.250 0.4817 0.01467 0.00699 -0.1632 0.9218 0.0754
-1.000 0.5151 0.01439 0.00676 -0.1645 0.9196 0.0930
-0.750 0.5495 0.01408 0.00665 -0.1660 0.9178 0.1512
-0.500 0.5848 0.01378 0.00652 -0.1677 0.9163 0.2177
-0.250 0.6117 0.01345 0.00667 -0.1679 0.9111 0.3744
0.000 0.6430 0.01296 0.00678 -0.1688 0.9075 0.5881
0.250 0.6638 0.01198 0.00650 -0.1663 0.9035 0.9681
0.750 0.7272 0.01154 0.00596 -0.1672 0.8903 1.0000
1.000 0.7584 0.01112 0.00549 -0.1673 0.8775 1.0000
1.250 0.7920 0.01069 0.00501 -0.1678 0.8623 1.0000
1.500 0.8255 0.01039 0.00469 -0.1685 0.8454 1.0000
1.750 0.8598 0.01022 0.00450 -0.1695 0.8311 1.0000
2.000 0.9020 0.00995 0.00422 -0.1721 0.8087 1.0000
2.250 0.9506 0.00970 0.00383 -0.1760 0.7687 1.0000
2.500 0.9900 0.00994 0.00360 -0.1778 0.6773 1.0000
2.750 1.0041 0.01100 0.00390 -0.1746 0.5518 1.0000
3.000 1.0221 0.01172 0.00431 -0.1726 0.5006 1.0000
3.250 1.0419 0.01234 0.00471 -0.1710 0.4437 1.0000
3.500 1.0546 0.01354 0.00525 -0.1682 0.3189 1.0000
3.750 1.0741 0.01434 0.00581 -0.1668 0.2654 1.0000
4.000 1.0939 0.01515 0.00635 -0.1655 0.2060 1.0000
4.250 1.1110 0.01633 0.00703 -0.1638 0.1124 1.0000
4.500 1.1309 0.01727 0.00773 -0.1625 0.0703 1.0000
4.750 1.1532 0.01790 0.00833 -0.1615 0.0564 1.0000
5.000 1.1756 0.01849 0.00896 -0.1605 0.0506 1.0000
5.250 1.1980 0.01907 0.00961 -0.1595 0.0481 1.0000
5.500 1.2203 0.01965 0.01032 -0.1584 0.0465 1.0000
5.750 1.2417 0.02030 0.01110 -0.1572 0.0445 1.0000
6.000 1.2618 0.02111 0.01197 -0.1559 0.0407 1.0000
6.250 1.2799 0.02212 0.01310 -0.1542 0.0370 1.0000
6.500 1.2999 0.02290 0.01401 -0.1529 0.0334 1.0000
6.750 1.3170 0.02405 0.01522 -0.1511 0.0295 1.0000
7.000 1.3356 0.02506 0.01636 -0.1496 0.0262 1.0000
7.250 1.3551 0.02595 0.01742 -0.1480 0.0218 1.0000
7.500 1.3730 0.02689 0.01842 -0.1464 0.0185 1.0000
7.750 1.3900 0.02812 0.01976 -0.1446 0.0160 1.0000
8.000 1.4074 0.02942 0.02128 -0.1428 0.0141 1.0000
8.250 1.4242 0.03066 0.02265 -0.1410 0.0127 1.0000
8.500 1.4397 0.03191 0.02401 -0.1391 0.0116 1.0000
8.750 1.4552 0.03403 0.02632 -0.1373 0.0104 1.0000
9.000 1.4718 0.03590 0.02846 -0.1355 0.0095 1.0000
9.250 1.4868 0.03820 0.03104 -0.1336 0.0089 1.0000
9.500 1.4989 0.04051 0.03364 -0.1313 0.0084 1.0000
9.750 1.5075 0.04284 0.03624 -0.1285 0.0081 1.0000
10.000 1.5126 0.04519 0.03885 -0.1255 0.0078 1.0000
10.250 1.5140 0.04791 0.04186 -0.1221 0.0076 1.0000
10.500 1.5104 0.05125 0.04552 -0.1184 0.0074 1.0000
10.750 1.5009 0.05526 0.04989 -0.1144 0.0072 1.0000
11.000 1.4898 0.05932 0.05433 -0.1106 0.0071 1.0000
11.250 1.4752 0.06378 0.05917 -0.1072 0.0071 1.0000
11.500 1.4571 0.06885 0.06466 -0.1044 0.0068 1.0000
11.750 1.4377 0.07412 0.07020 -0.1026 0.0069 1.0000
12.000 1.4159 0.08014 0.07653 -0.1019 0.0068 1.0000
12.250 1.3931 0.08683 0.08349 -0.1026 0.0068 1.0000
12.500 1.3715 0.09392 0.09080 -0.1048 0.0069 1.0000
12.750 1.3522 0.10138 0.09844 -0.1083 0.0070 1.0000
13.000 1.3312 0.11050 0.10775 -0.1139 0.0070 1.0000
13.250 1.3116 0.12059 0.11799 -0.1207 0.0071 1.0000
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Polar data table (+)
Polar graphs
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