EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 397 AIRFOIL (e397-il) Reynolds number: 500,000 Max Cl/Cd: 135.71 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e397-il-500000.txt Download as CSV file: xf-e397-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4873 0.07429 0.07157 -0.0867 0.9931 0.0074
-12.500 -0.5004 0.06540 0.06254 -0.0953 0.9886 0.0075
-12.250 -0.5077 0.05692 0.05388 -0.1051 0.9841 0.0075
-12.000 -0.5150 0.04915 0.04590 -0.1141 0.9755 0.0074
-11.750 -0.5124 0.04275 0.03931 -0.1227 0.9665 0.0073
-11.500 -0.5039 0.03668 0.03306 -0.1321 0.9578 0.0074
-11.000 -0.4624 0.02689 0.02281 -0.1526 0.9344 0.0078
-10.750 -0.4377 0.02445 0.02012 -0.1577 0.9228 0.0082
-10.500 -0.4162 0.02271 0.01815 -0.1601 0.9113 0.0086
-10.250 -0.3971 0.02125 0.01647 -0.1611 0.9001 0.0089
-10.000 -0.3778 0.02027 0.01529 -0.1611 0.8896 0.0093
-9.750 -0.3613 0.01868 0.01354 -0.1614 0.8802 0.0098
-9.500 -0.3400 0.01775 0.01249 -0.1615 0.8719 0.0104
-9.250 -0.3172 0.01698 0.01158 -0.1616 0.8643 0.0112
-9.000 -0.2934 0.01628 0.01071 -0.1616 0.8571 0.0121
-8.750 -0.2704 0.01530 0.00963 -0.1618 0.8507 0.0137
-8.500 -0.2457 0.01465 0.00887 -0.1619 0.8442 0.0158
-8.250 -0.2193 0.01414 0.00827 -0.1622 0.8388 0.0191
-8.000 -0.1941 0.01356 0.00764 -0.1622 0.8327 0.0238
-7.750 -0.1676 0.01310 0.00712 -0.1624 0.8272 0.0295
-7.500 -0.1402 0.01268 0.00665 -0.1628 0.8226 0.0360
-7.250 -0.1139 0.01226 0.00622 -0.1629 0.8172 0.0428
-7.000 -0.0866 0.01188 0.00580 -0.1631 0.8123 0.0500
-6.500 -0.0312 0.01133 0.00517 -0.1636 0.8031 0.0672
-6.250 -0.0034 0.01108 0.00490 -0.1638 0.7986 0.0770
-6.000 0.0249 0.01080 0.00459 -0.1642 0.7945 0.0889
-5.750 0.0530 0.01056 0.00434 -0.1645 0.7904 0.1015
-5.500 0.0809 0.01033 0.00413 -0.1647 0.7859 0.1155
-5.250 0.1092 0.01013 0.00392 -0.1649 0.7819 0.1307
-5.000 0.1382 0.00998 0.00374 -0.1653 0.7783 0.1466
-4.750 0.1664 0.00983 0.00360 -0.1655 0.7743 0.1626
-4.500 0.1946 0.00967 0.00347 -0.1658 0.7702 0.1799
-4.250 0.2232 0.00953 0.00334 -0.1661 0.7665 0.1979
-4.000 0.2524 0.00944 0.00324 -0.1665 0.7631 0.2161
-3.750 0.2807 0.00935 0.00317 -0.1667 0.7594 0.2340
-3.500 0.3091 0.00926 0.00310 -0.1669 0.7555 0.2514
-3.250 0.3378 0.00919 0.00303 -0.1672 0.7519 0.2691
-3.000 0.3669 0.00915 0.00297 -0.1675 0.7487 0.2868
-2.750 0.3956 0.00911 0.00294 -0.1678 0.7453 0.3038
-2.500 0.4238 0.00905 0.00292 -0.1679 0.7415 0.3210
-2.250 0.4524 0.00900 0.00289 -0.1682 0.7379 0.3382
-2.000 0.4813 0.00897 0.00286 -0.1684 0.7346 0.3558
-1.750 0.5107 0.00898 0.00287 -0.1688 0.7315 0.3733
-1.500 0.5385 0.00894 0.00288 -0.1689 0.7279 0.3915
-1.250 0.5669 0.00891 0.00289 -0.1691 0.7242 0.4101
-1.000 0.5956 0.00889 0.00289 -0.1693 0.7208 0.4294
-0.750 0.6248 0.00889 0.00291 -0.1697 0.7177 0.4495
-0.500 0.6531 0.00889 0.00297 -0.1699 0.7143 0.4704
0.000 0.7095 0.00885 0.00305 -0.1701 0.7070 0.5149
0.250 0.7383 0.00886 0.00309 -0.1704 0.7037 0.5391
0.500 0.7670 0.00889 0.00317 -0.1706 0.7004 0.5638
0.750 0.7943 0.00888 0.00326 -0.1706 0.6964 0.5895
1.000 0.8223 0.00887 0.00333 -0.1707 0.6925 0.6167
1.250 0.8505 0.00887 0.00338 -0.1708 0.6889 0.6443
1.500 0.8788 0.00891 0.00349 -0.1709 0.6852 0.6731
1.750 0.9053 0.00889 0.00359 -0.1707 0.6808 0.7024
2.000 0.9324 0.00888 0.00367 -0.1705 0.6764 0.7331
2.250 0.9598 0.00889 0.00374 -0.1704 0.6725 0.7653
2.500 0.9852 0.00889 0.00386 -0.1699 0.6679 0.7994
2.750 1.0095 0.00885 0.00395 -0.1691 0.6627 0.8372
3.000 1.0321 0.00881 0.00398 -0.1678 0.6580 0.8811
3.250 1.0523 0.00868 0.00399 -0.1659 0.6531 0.9743
3.500 1.0801 0.00873 0.00405 -0.1660 0.6475 1.0000
3.750 1.1083 0.00882 0.00408 -0.1662 0.6415 1.0000
4.000 1.1329 0.00884 0.00415 -0.1656 0.6320 1.0000
4.250 1.1584 0.00890 0.00418 -0.1651 0.6223 1.0000
4.500 1.1834 0.00898 0.00423 -0.1646 0.6125 1.0000
4.750 1.2086 0.00907 0.00436 -0.1642 0.6033 1.0000
5.000 1.2339 0.00920 0.00446 -0.1637 0.5951 1.0000
5.250 1.2585 0.00931 0.00460 -0.1632 0.5849 1.0000
5.500 1.2830 0.00946 0.00476 -0.1626 0.5753 1.0000
5.750 1.3067 0.00963 0.00492 -0.1619 0.5653 1.0000
6.000 1.3300 0.00980 0.00511 -0.1611 0.5536 1.0000
6.250 1.3525 0.01000 0.00531 -0.1601 0.5408 1.0000
6.500 1.3736 0.01024 0.00554 -0.1589 0.5260 1.0000
6.750 1.3924 0.01054 0.00580 -0.1573 0.5082 1.0000
7.000 1.4094 0.01090 0.00611 -0.1553 0.4874 1.0000
7.250 1.4222 0.01133 0.00646 -0.1526 0.4632 1.0000
7.500 1.4305 0.01188 0.00691 -0.1490 0.4348 1.0000
7.750 1.4371 0.01255 0.00745 -0.1453 0.4052 1.0000
8.000 1.4420 0.01335 0.00810 -0.1414 0.3740 1.0000
8.250 1.4444 0.01430 0.00889 -0.1372 0.3413 1.0000
8.500 1.4463 0.01536 0.00979 -0.1332 0.3088 1.0000
8.750 1.4485 0.01650 0.01078 -0.1295 0.2783 1.0000
9.000 1.4504 0.01775 0.01189 -0.1260 0.2489 1.0000
9.250 1.4521 0.01910 0.01310 -0.1226 0.2203 1.0000
9.500 1.4555 0.02045 0.01434 -0.1197 0.1951 1.0000
9.750 1.4588 0.02189 0.01567 -0.1169 0.1715 1.0000
10.000 1.4611 0.02348 0.01713 -0.1142 0.1487 1.0000
10.250 1.4634 0.02515 0.01869 -0.1116 0.1247 1.0000
10.500 1.4656 0.02691 0.02034 -0.1092 0.1038 1.0000
10.750 1.4675 0.02876 0.02210 -0.1069 0.0849 1.0000
11.000 1.4708 0.03059 0.02385 -0.1049 0.0678 1.0000
11.250 1.4746 0.03243 0.02562 -0.1030 0.0572 1.0000
11.500 1.4793 0.03426 0.02744 -0.1014 0.0513 1.0000
11.750 1.4869 0.03590 0.02914 -0.1000 0.0477 1.0000
12.000 1.4925 0.03774 0.03102 -0.0986 0.0442 1.0000
12.250 1.4952 0.03993 0.03325 -0.0971 0.0403 1.0000
12.500 1.5068 0.04132 0.03474 -0.0962 0.0372 1.0000
12.750 1.5118 0.04338 0.03682 -0.0951 0.0333 1.0000
13.000 1.5206 0.04511 0.03862 -0.0942 0.0291 1.0000
13.250 1.5260 0.04721 0.04071 -0.0932 0.0247 1.0000
13.500 1.5304 0.04949 0.04297 -0.0923 0.0204 1.0000
13.750 1.5343 0.05188 0.04541 -0.0914 0.0174 1.0000
14.000 1.5351 0.05470 0.04828 -0.0906 0.0150 1.0000
14.250 1.5363 0.05753 0.05116 -0.0899 0.0132 1.0000
14.500 1.5357 0.06067 0.05440 -0.0892 0.0118 1.0000
14.750 1.5377 0.06357 0.05740 -0.0888 0.0108 1.0000
15.000 1.5356 0.06706 0.06096 -0.0885 0.0100 1.0000
15.250 1.5319 0.07087 0.06489 -0.0882 0.0093 1.0000
15.500 1.5337 0.07402 0.06815 -0.0882 0.0086 1.0000
15.750 1.5341 0.07743 0.07165 -0.0883 0.0080 1.0000
16.000 1.5321 0.08125 0.07555 -0.0886 0.0076 1.0000
16.250 1.5220 0.08636 0.08077 -0.0891 0.0072 1.0000
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