EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 397 AIRFOIL (e397-il) Reynolds number: 200,000 Max Cl/Cd: 89.27 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e397-il-200000-n5.txt Download as CSV file: xf-e397-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 397 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3314 0.09818 0.09460 -0.0767 0.9842 0.0120
-12.000 -0.3779 0.08216 0.07846 -0.0862 0.9767 0.0117
-11.750 -0.4003 0.07192 0.06811 -0.0943 0.9679 0.0114
-11.500 -0.4191 0.06248 0.05850 -0.1028 0.9579 0.0112
-11.250 -0.4306 0.05443 0.05028 -0.1111 0.9468 0.0111
-11.000 -0.4349 0.04668 0.04228 -0.1209 0.9364 0.0112
-10.750 -0.4300 0.03993 0.03525 -0.1311 0.9262 0.0114
-10.500 -0.4215 0.03445 0.02944 -0.1402 0.9141 0.0116
-10.250 -0.4093 0.03061 0.02526 -0.1467 0.9016 0.0120
-10.000 -0.3945 0.02819 0.02262 -0.1495 0.8914 0.0124
-9.750 -0.3731 0.02629 0.02052 -0.1520 0.8843 0.0131
-9.500 -0.3554 0.02482 0.01886 -0.1528 0.8754 0.0140
-9.250 -0.3318 0.02339 0.01715 -0.1541 0.8692 0.0153
-9.000 -0.3116 0.02231 0.01596 -0.1545 0.8613 0.0169
-8.750 -0.2867 0.02129 0.01472 -0.1552 0.8554 0.0193
-8.500 -0.2638 0.02031 0.01364 -0.1557 0.8492 0.0217
-8.250 -0.2396 0.01938 0.01255 -0.1560 0.8432 0.0248
-8.000 -0.2123 0.01868 0.01168 -0.1567 0.8386 0.0294
-7.750 -0.1884 0.01802 0.01097 -0.1568 0.8323 0.0343
-7.500 -0.1620 0.01741 0.01027 -0.1572 0.8271 0.0403
-7.250 -0.1340 0.01686 0.00960 -0.1578 0.8230 0.0472
-6.750 -0.0817 0.01595 0.00854 -0.1581 0.8126 0.0622
-6.500 -0.0533 0.01551 0.00801 -0.1587 0.8086 0.0709
-6.250 -0.0267 0.01516 0.00760 -0.1588 0.8037 0.0806
-6.000 0.0005 0.01484 0.00721 -0.1590 0.7991 0.0913
-5.750 0.0288 0.01452 0.00682 -0.1594 0.7952 0.1033
-5.500 0.0572 0.01423 0.00649 -0.1598 0.7914 0.1164
-5.250 0.0841 0.01399 0.00623 -0.1599 0.7866 0.1301
-5.000 0.1121 0.01376 0.00597 -0.1601 0.7825 0.1453
-4.750 0.1409 0.01356 0.00571 -0.1605 0.7790 0.1615
-4.500 0.1690 0.01339 0.00552 -0.1608 0.7752 0.1778
-4.250 0.1964 0.01324 0.00536 -0.1609 0.7707 0.1944
-4.000 0.2246 0.01310 0.00521 -0.1611 0.7669 0.2117
-3.750 0.2536 0.01297 0.00506 -0.1615 0.7637 0.2299
-3.500 0.2818 0.01288 0.00495 -0.1617 0.7600 0.2474
-3.250 0.3092 0.01280 0.00488 -0.1618 0.7557 0.2648
-3.000 0.3374 0.01273 0.00480 -0.1620 0.7520 0.2823
-2.750 0.3663 0.01267 0.00470 -0.1623 0.7489 0.3000
-2.500 0.3949 0.01263 0.00464 -0.1625 0.7455 0.3175
-2.250 0.4220 0.01260 0.00464 -0.1625 0.7413 0.3343
-2.000 0.4500 0.01256 0.00462 -0.1626 0.7376 0.3519
-1.750 0.4786 0.01253 0.00458 -0.1628 0.7343 0.3697
-1.500 0.5078 0.01250 0.00455 -0.1632 0.7314 0.3881
-1.250 0.5344 0.01251 0.00461 -0.1631 0.7272 0.4063
-1.000 0.5619 0.01251 0.00465 -0.1631 0.7233 0.4252
-0.750 0.5903 0.01251 0.00466 -0.1633 0.7199 0.4451
-0.500 0.6194 0.01250 0.00467 -0.1636 0.7170 0.4652
-0.250 0.6460 0.01253 0.00478 -0.1634 0.7130 0.4862
0.250 0.7008 0.01256 0.00493 -0.1634 0.7054 0.5308
0.500 0.7295 0.01257 0.00498 -0.1636 0.7024 0.5554
0.750 0.7559 0.01261 0.00512 -0.1634 0.6984 0.5796
1.000 0.7820 0.01266 0.00526 -0.1631 0.6942 0.6054
1.250 0.8090 0.01268 0.00536 -0.1629 0.6904 0.6321
1.500 0.8368 0.01270 0.00543 -0.1629 0.6872 0.6604
1.750 0.8619 0.01276 0.00562 -0.1624 0.6829 0.6890
2.000 0.8866 0.01280 0.00578 -0.1617 0.6783 0.7194
2.250 0.9120 0.01282 0.00589 -0.1612 0.6743 0.7519
2.500 0.9376 0.01282 0.00596 -0.1605 0.6707 0.7874
2.750 0.9578 0.01286 0.00616 -0.1589 0.6653 0.8272
3.000 0.9779 0.01282 0.00623 -0.1571 0.6604 0.8789
3.250 1.0054 0.01271 0.00616 -0.1568 0.6563 1.0000
3.500 1.0302 0.01289 0.00639 -0.1564 0.6502 1.0000
3.750 1.0572 0.01301 0.00651 -0.1564 0.6445 1.0000
4.000 1.0847 0.01312 0.00662 -0.1564 0.6390 1.0000
4.250 1.1091 0.01327 0.00683 -0.1559 0.6319 1.0000
4.500 1.1371 0.01337 0.00689 -0.1560 0.6261 1.0000
4.750 1.1600 0.01355 0.00715 -0.1552 0.6181 1.0000
5.000 1.1868 0.01364 0.00724 -0.1550 0.6110 1.0000
5.250 1.2089 0.01382 0.00748 -0.1540 0.6010 1.0000
5.500 1.2318 0.01395 0.00764 -0.1531 0.5900 1.0000
5.750 1.2533 0.01409 0.00779 -0.1519 0.5764 1.0000
6.000 1.2730 0.01426 0.00795 -0.1503 0.5597 1.0000
6.250 1.2916 0.01449 0.00815 -0.1486 0.5412 1.0000
6.500 1.3092 0.01477 0.00837 -0.1467 0.5215 1.0000
6.750 1.3262 0.01510 0.00869 -0.1448 0.5026 1.0000
7.000 1.3414 0.01546 0.00904 -0.1425 0.4847 1.0000
7.250 1.3545 0.01590 0.00944 -0.1399 0.4656 1.0000
7.500 1.3656 0.01643 0.00992 -0.1371 0.4451 1.0000
7.750 1.3754 0.01705 0.01048 -0.1341 0.4225 1.0000
8.000 1.3821 0.01782 0.01118 -0.1308 0.3986 1.0000
8.250 1.3856 0.01878 0.01203 -0.1271 0.3714 1.0000
8.500 1.3879 0.01988 0.01302 -0.1235 0.3440 1.0000
8.750 1.3900 0.02110 0.01415 -0.1201 0.3181 1.0000
9.000 1.3908 0.02250 0.01543 -0.1167 0.2921 1.0000
9.250 1.3922 0.02398 0.01682 -0.1137 0.2675 1.0000
9.500 1.3957 0.02544 0.01824 -0.1111 0.2464 1.0000
9.750 1.3997 0.02695 0.01970 -0.1087 0.2267 1.0000
10.000 1.4021 0.02864 0.02133 -0.1063 0.2068 1.0000
10.250 1.4044 0.03044 0.02306 -0.1041 0.1848 1.0000
10.500 1.4050 0.03245 0.02497 -0.1019 0.1633 1.0000
10.750 1.4069 0.03443 0.02688 -0.0999 0.1417 1.0000
11.000 1.4083 0.03655 0.02891 -0.0981 0.1223 1.0000
11.250 1.4110 0.03862 0.03093 -0.0965 0.1052 1.0000
11.500 1.4141 0.04072 0.03302 -0.0950 0.0907 1.0000
11.750 1.4177 0.04285 0.03513 -0.0936 0.0768 1.0000
12.000 1.4205 0.04512 0.03737 -0.0923 0.0638 1.0000
12.250 1.4232 0.04747 0.03969 -0.0912 0.0561 1.0000
12.500 1.4252 0.04996 0.04218 -0.0901 0.0506 1.0000
12.750 1.4297 0.05226 0.04456 -0.0892 0.0463 1.0000
13.000 1.4315 0.05489 0.04725 -0.0883 0.0425 1.0000
13.250 1.4345 0.05748 0.04994 -0.0876 0.0391 1.0000
13.500 1.4402 0.05980 0.05240 -0.0870 0.0353 1.0000
13.750 1.4409 0.06278 0.05543 -0.0865 0.0321 1.0000
14.000 1.4477 0.06506 0.05785 -0.0861 0.0285 1.0000
14.250 1.4503 0.06791 0.06074 -0.0858 0.0254 1.0000
14.500 1.4545 0.07062 0.06356 -0.0856 0.0223 1.0000
14.750 1.4557 0.07378 0.06676 -0.0855 0.0201 1.0000
15.000 1.4572 0.07697 0.07008 -0.0854 0.0182 1.0000
15.250 1.4568 0.08048 0.07365 -0.0856 0.0165 1.0000
15.500 1.4553 0.08422 0.07752 -0.0859 0.0152 1.0000
15.750 1.4544 0.08797 0.08139 -0.0863 0.0139 1.0000
16.000 1.4517 0.09205 0.08557 -0.0869 0.0129 1.0000
16.250 1.4478 0.09640 0.09003 -0.0877 0.0121 1.0000
16.500 1.4451 0.10061 0.09441 -0.0886 0.0114 1.0000
16.750 1.4417 0.10502 0.09895 -0.0897 0.0108 1.0000
17.000 1.4377 0.10959 0.10365 -0.0910 0.0103 1.0000
17.250 1.4327 0.11439 0.10858 -0.0926 0.0099 1.0000
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Polar data table (+)
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