EPPLER 587 AIRFOIL (e587-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 587 AIRFOIL (e587-il) Reynolds number: 1,000,000 Max Cl/Cd: 145.92 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e587-il-1000000.txt Download as CSV file: xf-e587-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2550 0.03965 0.03712 -0.1590 0.9305 0.0060
-11.000 -0.2514 0.03330 0.03033 -0.1689 0.9050 0.0058
-10.750 -0.2744 0.02896 0.02551 -0.1685 0.8751 0.0055
-10.500 -0.3240 0.02293 0.01866 -0.1626 0.8514 0.0049
-10.250 -0.3258 0.02127 0.01675 -0.1597 0.8396 0.0048
-10.000 -0.3239 0.02007 0.01535 -0.1568 0.8303 0.0048
-9.750 -0.3183 0.01910 0.01421 -0.1543 0.8220 0.0048
-9.500 -0.3059 0.01817 0.01314 -0.1528 0.8154 0.0049
-9.250 -0.2918 0.01724 0.01207 -0.1513 0.8091 0.0049
-9.000 -0.2745 0.01660 0.01131 -0.1503 0.8036 0.0050
-8.750 -0.2568 0.01588 0.01051 -0.1492 0.7989 0.0051
-8.500 -0.2375 0.01527 0.00981 -0.1483 0.7940 0.0053
-8.250 -0.2176 0.01470 0.00914 -0.1475 0.7892 0.0055
-8.000 -0.1963 0.01420 0.00855 -0.1469 0.7851 0.0059
-7.750 -0.1737 0.01377 0.00807 -0.1464 0.7811 0.0062
-7.500 -0.1514 0.01331 0.00753 -0.1459 0.7771 0.0063
-7.250 -0.1319 0.01253 0.00665 -0.1452 0.7730 0.0068
-7.000 -0.1079 0.01213 0.00622 -0.1450 0.7694 0.0071
-6.750 -0.0833 0.01178 0.00585 -0.1448 0.7660 0.0074
-6.500 -0.0583 0.01142 0.00545 -0.1447 0.7625 0.0078
-6.250 -0.0327 0.01112 0.00509 -0.1447 0.7591 0.0082
-6.000 -0.0063 0.01084 0.00473 -0.1448 0.7553 0.0086
-5.750 0.0194 0.01043 0.00431 -0.1449 0.7525 0.0095
-5.500 0.0463 0.01017 0.00402 -0.1450 0.7494 0.0108
-5.250 0.0733 0.00988 0.00373 -0.1452 0.7462 0.0136
-5.000 0.1003 0.00951 0.00340 -0.1455 0.7429 0.0256
-4.750 0.1283 0.00924 0.00318 -0.1460 0.7394 0.0456
-4.500 0.1561 0.00896 0.00300 -0.1464 0.7367 0.0683
-4.250 0.1841 0.00863 0.00282 -0.1470 0.7337 0.1043
-4.000 0.2125 0.00824 0.00262 -0.1477 0.7306 0.1612
-3.750 0.2416 0.00768 0.00240 -0.1488 0.7275 0.2636
-3.500 0.2731 0.00666 0.00207 -0.1510 0.7242 0.4838
-3.250 0.3031 0.00648 0.00207 -0.1518 0.7213 0.5569
-3.000 0.3323 0.00647 0.00206 -0.1522 0.7185 0.5788
-2.750 0.3614 0.00648 0.00206 -0.1526 0.7153 0.5935
-2.500 0.3904 0.00651 0.00208 -0.1529 0.7122 0.6058
-2.250 0.4197 0.00658 0.00208 -0.1533 0.7090 0.6145
-2.000 0.4488 0.00664 0.00212 -0.1537 0.7058 0.6216
-1.750 0.4777 0.00668 0.00213 -0.1540 0.7028 0.6279
-1.500 0.5062 0.00670 0.00216 -0.1542 0.6995 0.6341
-1.250 0.5348 0.00678 0.00221 -0.1545 0.6962 0.6414
-1.000 0.5635 0.00687 0.00225 -0.1548 0.6926 0.6483
-0.750 0.5919 0.00694 0.00233 -0.1549 0.6892 0.6538
-0.500 0.6202 0.00697 0.00237 -0.1552 0.6857 0.6578
-0.250 0.6486 0.00700 0.00237 -0.1554 0.6819 0.6602
0.000 0.6771 0.00705 0.00237 -0.1557 0.6781 0.6620
0.250 0.7054 0.00707 0.00237 -0.1560 0.6742 0.6643
0.500 0.7333 0.00706 0.00238 -0.1562 0.6703 0.6663
0.750 0.7611 0.00708 0.00240 -0.1563 0.6659 0.6683
1.000 0.7888 0.00714 0.00243 -0.1565 0.6615 0.6704
1.250 0.8166 0.00719 0.00247 -0.1566 0.6573 0.6725
1.500 0.8444 0.00721 0.00250 -0.1568 0.6529 0.6745
1.750 0.8719 0.00726 0.00253 -0.1569 0.6483 0.6764
2.000 0.8992 0.00735 0.00258 -0.1570 0.6434 0.6782
2.250 0.9266 0.00735 0.00261 -0.1571 0.6384 0.6803
2.500 0.9532 0.00738 0.00265 -0.1570 0.6325 0.6825
2.750 0.9794 0.00746 0.00272 -0.1569 0.6269 0.6845
3.000 1.0064 0.00749 0.00278 -0.1569 0.6210 0.6864
3.250 1.0323 0.00758 0.00286 -0.1567 0.6149 0.6884
3.500 1.0585 0.00765 0.00294 -0.1566 0.6089 0.6905
3.750 1.0843 0.00773 0.00301 -0.1564 0.6018 0.6927
4.000 1.1092 0.00784 0.00311 -0.1560 0.5946 0.6947
4.250 1.1344 0.00792 0.00320 -0.1557 0.5864 0.6967
4.500 1.1583 0.00802 0.00330 -0.1551 0.5782 0.6990
4.750 1.1821 0.00813 0.00342 -0.1545 0.5689 0.7011
5.000 1.2053 0.00826 0.00355 -0.1538 0.5592 0.7033
5.250 1.2262 0.00843 0.00369 -0.1526 0.5486 0.7055
5.500 1.2464 0.00858 0.00384 -0.1513 0.5366 0.7080
5.750 1.2660 0.00876 0.00400 -0.1498 0.5240 0.7104
6.000 1.2841 0.00899 0.00419 -0.1481 0.5103 0.7123
6.250 1.3018 0.00923 0.00442 -0.1463 0.4958 0.7151
6.500 1.3189 0.00952 0.00468 -0.1445 0.4803 0.7176
6.750 1.3342 0.00986 0.00498 -0.1423 0.4626 0.7200
7.000 1.3492 0.01024 0.00531 -0.1401 0.4447 0.7226
7.250 1.3624 0.01069 0.00569 -0.1377 0.4255 0.7253
7.500 1.3749 0.01117 0.00610 -0.1352 0.4059 0.7280
7.750 1.3869 0.01168 0.00655 -0.1326 0.3851 0.7309
8.000 1.3976 0.01226 0.00706 -0.1299 0.3646 0.7340
8.250 1.4077 0.01288 0.00763 -0.1272 0.3458 0.7370
8.500 1.4176 0.01355 0.00823 -0.1245 0.3259 0.7400
8.750 1.4270 0.01427 0.00889 -0.1218 0.3061 0.7431
9.000 1.4353 0.01508 0.00962 -0.1191 0.2868 0.7461
9.250 1.4417 0.01599 0.01047 -0.1162 0.2668 0.7498
9.500 1.4487 0.01695 0.01136 -0.1135 0.2461 0.7536
9.750 1.4558 0.01795 0.01230 -0.1109 0.2275 0.7576
10.000 1.4594 0.01920 0.01344 -0.1080 0.2062 0.7613
10.250 1.4668 0.02029 0.01449 -0.1057 0.1903 0.7655
10.500 1.4729 0.02149 0.01565 -0.1034 0.1727 0.7698
10.750 1.4766 0.02292 0.01699 -0.1009 0.1530 0.7745
11.000 1.4809 0.02436 0.01836 -0.0987 0.1364 0.7791
11.250 1.4859 0.02580 0.01976 -0.0966 0.1216 0.7844
11.500 1.4901 0.02737 0.02127 -0.0945 0.1064 0.7904
11.750 1.4964 0.02884 0.02272 -0.0928 0.0949 0.7966
12.000 1.5018 0.03041 0.02428 -0.0911 0.0836 0.8037
12.250 1.5086 0.03194 0.02580 -0.0896 0.0743 0.8113
12.500 1.5143 0.03358 0.02745 -0.0881 0.0649 0.8203
12.750 1.5197 0.03530 0.02918 -0.0866 0.0567 0.8307
13.000 1.5251 0.03704 0.03095 -0.0852 0.0494 0.8439
13.250 1.5291 0.03891 0.03285 -0.0838 0.0425 0.8623
13.500 1.5329 0.04061 0.03467 -0.0822 0.0375 0.9008
13.750 1.5358 0.04235 0.03650 -0.0806 0.0321 1.0000
14.000 1.5415 0.04435 0.03851 -0.0797 0.0282 1.0000
14.250 1.5467 0.04644 0.04061 -0.0789 0.0244 1.0000
14.500 1.5518 0.04859 0.04278 -0.0782 0.0214 1.0000
14.750 1.5571 0.05078 0.04499 -0.0775 0.0185 1.0000
15.000 1.5623 0.05301 0.04726 -0.0769 0.0165 1.0000
15.250 1.5668 0.05537 0.04966 -0.0765 0.0146 1.0000
15.500 1.5716 0.05773 0.05206 -0.0760 0.0130 1.0000
15.750 1.5752 0.06029 0.05467 -0.0757 0.0116 1.0000
16.000 1.5793 0.06285 0.05728 -0.0755 0.0103 1.0000
16.250 1.5825 0.06554 0.06002 -0.0753 0.0092 1.0000
16.500 1.5852 0.06836 0.06291 -0.0752 0.0083 1.0000
16.750 1.5875 0.07128 0.06588 -0.0752 0.0073 1.0000
17.000 1.5892 0.07434 0.06900 -0.0754 0.0065 1.0000
17.250 1.5905 0.07750 0.07224 -0.0756 0.0058 1.0000
17.500 1.5897 0.08101 0.07582 -0.0759 0.0051 1.0000
17.750 1.5910 0.08426 0.07914 -0.0764 0.0046 1.0000
18.000 1.5895 0.08798 0.08294 -0.0770 0.0040 1.0000
18.250 1.5871 0.09189 0.08693 -0.0777 0.0036 1.0000
18.500 1.5859 0.09569 0.09081 -0.0785 0.0032 1.0000
18.750 1.5827 0.09983 0.09503 -0.0795 0.0028 1.0000
19.000 1.5784 0.10419 0.09948 -0.0807 0.0024 1.0000
19.250 1.5746 0.10851 0.10390 -0.0820 0.0021 1.0000
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