EPPLER 587 AIRFOIL (e587-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 587 AIRFOIL (e587-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.53 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e587-il-1000000-n5.txt Download as CSV file: xf-e587-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 587 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.4530 0.07856 0.07640 -0.1070 0.9750 0.0025
-14.250 -0.5340 0.05663 0.05412 -0.1206 0.9662 0.0025
-14.000 -0.5474 0.04888 0.04617 -0.1278 0.9570 0.0024
-13.750 -0.5515 0.04193 0.03895 -0.1363 0.9474 0.0024
-13.500 -0.5383 0.03643 0.03317 -0.1455 0.9374 0.0025
-13.250 -0.5090 0.03210 0.02856 -0.1555 0.9278 0.0025
-13.000 -0.4802 0.02890 0.02505 -0.1632 0.9081 0.0025
-12.500 -0.4626 0.02556 0.02123 -0.1643 0.8638 0.0025
-12.250 -0.4598 0.02419 0.01968 -0.1629 0.8484 0.0026
-12.000 -0.4560 0.02299 0.01832 -0.1614 0.8354 0.0026
-11.750 -0.4460 0.02217 0.01739 -0.1602 0.8249 0.0026
-11.500 -0.4395 0.02114 0.01623 -0.1586 0.8159 0.0026
-11.250 -0.4293 0.02036 0.01534 -0.1571 0.8076 0.0026
-11.000 -0.4225 0.01940 0.01426 -0.1553 0.8006 0.0026
-10.750 -0.4134 0.01862 0.01338 -0.1535 0.7936 0.0027
-10.500 -0.4120 0.01762 0.01224 -0.1505 0.7867 0.0028
-10.250 -0.4048 0.01687 0.01140 -0.1483 0.7810 0.0029
-10.000 -0.3896 0.01628 0.01073 -0.1471 0.7758 0.0030
-9.750 -0.3721 0.01580 0.01017 -0.1461 0.7712 0.0031
-9.500 -0.3525 0.01533 0.00965 -0.1454 0.7670 0.0032
-9.250 -0.3334 0.01480 0.00905 -0.1445 0.7626 0.0032
-9.000 -0.3119 0.01446 0.00865 -0.1440 0.7585 0.0034
-8.750 -0.2908 0.01404 0.00815 -0.1434 0.7549 0.0035
-8.500 -0.2680 0.01364 0.00772 -0.1430 0.7516 0.0037
-8.250 -0.2452 0.01325 0.00728 -0.1426 0.7478 0.0038
-8.000 -0.2219 0.01289 0.00686 -0.1423 0.7441 0.0040
-7.750 -0.1982 0.01256 0.00647 -0.1420 0.7407 0.0041
-7.500 -0.1737 0.01225 0.00611 -0.1418 0.7378 0.0042
-7.250 -0.1486 0.01193 0.00575 -0.1418 0.7347 0.0043
-7.000 -0.1233 0.01162 0.00540 -0.1417 0.7314 0.0044
-6.750 -0.0982 0.01128 0.00503 -0.1416 0.7281 0.0047
-6.500 -0.0725 0.01101 0.00471 -0.1416 0.7250 0.0050
-6.250 -0.0462 0.01077 0.00444 -0.1417 0.7222 0.0053
-6.000 -0.0191 0.01053 0.00418 -0.1419 0.7195 0.0058
-5.750 0.0080 0.01033 0.00395 -0.1421 0.7163 0.0063
-5.500 0.0351 0.01009 0.00370 -0.1423 0.7133 0.0075
-5.250 0.0623 0.00990 0.00349 -0.1425 0.7103 0.0092
-4.750 0.1175 0.00948 0.00309 -0.1431 0.7046 0.0192
-4.500 0.1457 0.00928 0.00292 -0.1435 0.7017 0.0286
-4.250 0.1738 0.00907 0.00276 -0.1440 0.6986 0.0409
-4.000 0.2019 0.00886 0.00261 -0.1444 0.6954 0.0600
-3.750 0.2300 0.00864 0.00246 -0.1449 0.6924 0.0866
-3.500 0.2588 0.00831 0.00231 -0.1456 0.6896 0.1387
-3.250 0.2883 0.00793 0.00215 -0.1466 0.6866 0.2051
-3.000 0.3180 0.00758 0.00200 -0.1475 0.6835 0.2753
-2.750 0.3480 0.00717 0.00184 -0.1487 0.6802 0.3650
-2.500 0.3790 0.00663 0.00170 -0.1501 0.6770 0.5005
-2.250 0.4085 0.00654 0.00169 -0.1507 0.6741 0.5457
-2.000 0.4378 0.00651 0.00170 -0.1512 0.6709 0.5662
-1.750 0.4668 0.00652 0.00170 -0.1516 0.6674 0.5800
-1.500 0.4955 0.00654 0.00172 -0.1519 0.6638 0.5919
-1.250 0.5238 0.00659 0.00174 -0.1521 0.6601 0.6038
-1.000 0.5526 0.00663 0.00178 -0.1525 0.6567 0.6155
-0.750 0.5813 0.00667 0.00182 -0.1527 0.6526 0.6239
-0.500 0.6095 0.00672 0.00183 -0.1530 0.6482 0.6280
-0.250 0.6372 0.00677 0.00184 -0.1531 0.6440 0.6301
0.000 0.6657 0.00679 0.00187 -0.1534 0.6399 0.6321
0.250 0.6938 0.00683 0.00189 -0.1536 0.6350 0.6341
0.500 0.7212 0.00689 0.00192 -0.1537 0.6298 0.6363
0.750 0.7489 0.00694 0.00196 -0.1538 0.6248 0.6384
1.000 0.7766 0.00700 0.00200 -0.1540 0.6190 0.6404
1.250 0.8033 0.00708 0.00204 -0.1539 0.6132 0.6422
1.500 0.8310 0.00713 0.00208 -0.1541 0.6079 0.6440
1.750 0.8581 0.00720 0.00214 -0.1541 0.6018 0.6458
2.000 0.8842 0.00729 0.00220 -0.1539 0.5956 0.6479
2.250 0.9111 0.00735 0.00227 -0.1539 0.5884 0.6498
2.500 0.9363 0.00746 0.00236 -0.1536 0.5802 0.6517
2.750 0.9624 0.00755 0.00244 -0.1534 0.5715 0.6536
3.000 0.9873 0.00768 0.00254 -0.1530 0.5631 0.6555
3.250 1.0127 0.00779 0.00263 -0.1527 0.5541 0.6575
3.500 1.0371 0.00792 0.00275 -0.1523 0.5448 0.6596
4.000 1.0838 0.00824 0.00300 -0.1509 0.5222 0.6632
4.250 1.1053 0.00841 0.00315 -0.1498 0.5095 0.6651
4.500 1.1250 0.00861 0.00331 -0.1484 0.4955 0.6670
4.750 1.1443 0.00882 0.00349 -0.1469 0.4817 0.6690
5.000 1.1626 0.00909 0.00371 -0.1453 0.4658 0.6712
5.250 1.1806 0.00938 0.00395 -0.1436 0.4490 0.6735
5.500 1.1982 0.00971 0.00421 -0.1418 0.4315 0.6757
5.750 1.2145 0.01007 0.00451 -0.1399 0.4134 0.6777
6.000 1.2311 0.01044 0.00481 -0.1380 0.3966 0.6795
6.250 1.2450 0.01090 0.00519 -0.1357 0.3761 0.6816
6.500 1.2606 0.01130 0.00555 -0.1337 0.3600 0.6837
6.750 1.2757 0.01173 0.00594 -0.1317 0.3430 0.6859
7.000 1.2897 0.01221 0.00636 -0.1296 0.3261 0.6884
7.250 1.3033 0.01273 0.00682 -0.1274 0.3089 0.6909
7.500 1.3165 0.01327 0.00731 -0.1252 0.2933 0.6934
7.750 1.3283 0.01389 0.00787 -0.1229 0.2751 0.6955
8.000 1.3398 0.01454 0.00846 -0.1205 0.2581 0.6978
8.250 1.3501 0.01526 0.00913 -0.1181 0.2409 0.7002
8.500 1.3613 0.01599 0.00982 -0.1159 0.2259 0.7027
8.750 1.3722 0.01676 0.01055 -0.1137 0.2114 0.7054
9.000 1.3812 0.01766 0.01139 -0.1114 0.1950 0.7082
9.250 1.3912 0.01855 0.01223 -0.1092 0.1810 0.7110
9.500 1.3989 0.01959 0.01322 -0.1069 0.1646 0.7137
9.750 1.4061 0.02072 0.01429 -0.1046 0.1485 0.7167
10.000 1.4121 0.02196 0.01547 -0.1023 0.1311 0.7197
10.250 1.4203 0.02312 0.01659 -0.1004 0.1187 0.7228
10.500 1.4273 0.02441 0.01783 -0.0984 0.1050 0.7259
10.750 1.4320 0.02589 0.01923 -0.0963 0.0887 0.7287
11.000 1.4387 0.02729 0.02060 -0.0944 0.0767 0.7320
11.250 1.4454 0.02874 0.02203 -0.0927 0.0663 0.7358
11.500 1.4483 0.03051 0.02374 -0.0908 0.0529 0.7397
11.750 1.4549 0.03207 0.02527 -0.0892 0.0444 0.7436
12.000 1.4615 0.03368 0.02687 -0.0878 0.0371 0.7473
12.250 1.4699 0.03517 0.02840 -0.0866 0.0323 0.7515
12.500 1.4770 0.03682 0.03005 -0.0854 0.0270 0.7560
12.750 1.4844 0.03848 0.03174 -0.0843 0.0231 0.7604
13.000 1.4922 0.04016 0.03345 -0.0832 0.0198 0.7650
13.250 1.4988 0.04198 0.03530 -0.0822 0.0166 0.7703
13.500 1.5073 0.04366 0.03703 -0.0814 0.0146 0.7762
13.750 1.5134 0.04561 0.03903 -0.0805 0.0121 0.7824
14.000 1.5208 0.04748 0.04096 -0.0798 0.0107 0.7896
14.250 1.5278 0.04942 0.04297 -0.0791 0.0093 0.7969
14.500 1.5345 0.05145 0.04506 -0.0785 0.0081 0.8055
14.750 1.5400 0.05363 0.04731 -0.0780 0.0066 0.8142
15.000 1.5464 0.05576 0.04953 -0.0775 0.0060 0.8247
15.250 1.5518 0.05801 0.05187 -0.0771 0.0052 0.8373
15.500 1.5564 0.06039 0.05435 -0.0767 0.0044 0.8538
15.750 1.5607 0.06274 0.05683 -0.0762 0.0039 0.8804
16.000 1.5612 0.06499 0.05927 -0.0752 0.0034 1.0000
16.250 1.5653 0.06763 0.06198 -0.0751 0.0031 1.0000
16.500 1.5691 0.07036 0.06477 -0.0751 0.0028 1.0000
16.750 1.5713 0.07335 0.06783 -0.0752 0.0025 1.0000
17.000 1.5741 0.07630 0.07086 -0.0754 0.0022 1.0000
17.250 1.5761 0.07942 0.07404 -0.0757 0.0019 1.0000
17.500 1.5764 0.08281 0.07752 -0.0761 0.0017 1.0000
17.750 1.5772 0.08618 0.08097 -0.0766 0.0015 1.0000
18.000 1.5779 0.08962 0.08449 -0.0772 0.0013 1.0000
18.250 1.5774 0.09329 0.08824 -0.0780 0.0012 1.0000
18.500 1.5759 0.09715 0.09219 -0.0789 0.0010 1.0000
18.750 1.5739 0.10113 0.09625 -0.0799 0.0009 1.0000
19.000 1.5720 0.10512 0.10033 -0.0810 0.0008 1.0000
19.250 1.5700 0.10917 0.10446 -0.0823 0.0008 1.0000
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Polar data table (+)
Polar graphs
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