EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 397 AIRFOIL (e397-il) Reynolds number: 500,000 Max Cl/Cd: 125.95 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e397-il-500000-n5.txt Download as CSV file: xf-e397-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4739 0.08266 0.07973 -0.0866 0.9871 0.0043
-13.250 -0.4902 0.07402 0.07098 -0.0936 0.9827 0.0044
-12.750 -0.5299 0.05838 0.05512 -0.1057 0.9587 0.0042
-12.500 -0.5435 0.04901 0.04556 -0.1164 0.9463 0.0042
-12.250 -0.5375 0.04010 0.03640 -0.1305 0.9354 0.0043
-12.000 -0.5215 0.03207 0.02806 -0.1454 0.9190 0.0043
-11.750 -0.5146 0.02710 0.02278 -0.1536 0.8958 0.0043
-11.500 -0.5098 0.02440 0.01980 -0.1569 0.8772 0.0044
-11.250 -0.4983 0.02284 0.01804 -0.1575 0.8650 0.0045
-11.000 -0.4834 0.02158 0.01658 -0.1578 0.8547 0.0047
-10.750 -0.4662 0.02051 0.01534 -0.1578 0.8456 0.0049
-10.500 -0.4471 0.01951 0.01416 -0.1579 0.8376 0.0051
-10.250 -0.4274 0.01850 0.01301 -0.1580 0.8297 0.0053
-10.000 -0.4055 0.01771 0.01208 -0.1581 0.8231 0.0057
-9.750 -0.3825 0.01699 0.01124 -0.1581 0.8168 0.0061
-9.500 -0.3586 0.01635 0.01046 -0.1582 0.8107 0.0066
-9.250 -0.3341 0.01576 0.00974 -0.1583 0.8052 0.0071
-9.000 -0.3094 0.01514 0.00903 -0.1585 0.7992 0.0079
-8.750 -0.2839 0.01466 0.00843 -0.1586 0.7940 0.0092
-8.500 -0.2581 0.01413 0.00784 -0.1588 0.7892 0.0109
-8.250 -0.2320 0.01366 0.00731 -0.1590 0.7842 0.0133
-8.000 -0.2055 0.01325 0.00681 -0.1591 0.7794 0.0161
-7.750 -0.1787 0.01285 0.00637 -0.1593 0.7750 0.0201
-7.500 -0.1516 0.01249 0.00597 -0.1596 0.7703 0.0245
-7.250 -0.1244 0.01216 0.00560 -0.1598 0.7660 0.0293
-7.000 -0.0969 0.01185 0.00524 -0.1600 0.7622 0.0346
-6.750 -0.0693 0.01154 0.00493 -0.1603 0.7580 0.0412
-6.500 -0.0416 0.01126 0.00463 -0.1605 0.7537 0.0487
-6.250 -0.0137 0.01103 0.00436 -0.1608 0.7497 0.0562
-6.000 0.0144 0.01081 0.00410 -0.1610 0.7463 0.0644
-5.750 0.0425 0.01057 0.00387 -0.1613 0.7425 0.0736
-5.500 0.0707 0.01036 0.00366 -0.1616 0.7385 0.0838
-5.250 0.0990 0.01018 0.00345 -0.1618 0.7348 0.0949
-5.000 0.1273 0.01003 0.00327 -0.1621 0.7316 0.1064
-4.750 0.1558 0.00986 0.00312 -0.1623 0.7281 0.1184
-4.500 0.1842 0.00971 0.00297 -0.1626 0.7243 0.1321
-4.250 0.2127 0.00957 0.00283 -0.1629 0.7207 0.1464
-4.000 0.2412 0.00946 0.00271 -0.1631 0.7176 0.1612
-3.750 0.2698 0.00934 0.00262 -0.1634 0.7144 0.1764
-3.500 0.2984 0.00924 0.00253 -0.1637 0.7108 0.1910
-3.250 0.3269 0.00915 0.00245 -0.1639 0.7073 0.2067
-3.000 0.3554 0.00908 0.00238 -0.1642 0.7041 0.2227
-2.750 0.3840 0.00903 0.00232 -0.1644 0.7012 0.2380
-2.500 0.4126 0.00895 0.00228 -0.1646 0.6978 0.2537
-2.250 0.4412 0.00890 0.00225 -0.1649 0.6944 0.2690
-2.000 0.4697 0.00885 0.00222 -0.1651 0.6910 0.2846
-1.750 0.4982 0.00883 0.00220 -0.1653 0.6879 0.2994
-1.500 0.5267 0.00880 0.00219 -0.1655 0.6849 0.3151
-1.250 0.5552 0.00876 0.00219 -0.1657 0.6815 0.3304
-1.000 0.5836 0.00874 0.00220 -0.1659 0.6779 0.3461
-0.750 0.6120 0.00873 0.00221 -0.1661 0.6746 0.3620
-0.500 0.6404 0.00874 0.00222 -0.1663 0.6716 0.3782
-0.250 0.6687 0.00872 0.00226 -0.1665 0.6682 0.3949
0.000 0.6970 0.00871 0.00230 -0.1666 0.6646 0.4120
0.250 0.7251 0.00871 0.00234 -0.1668 0.6610 0.4298
0.500 0.7533 0.00872 0.00238 -0.1669 0.6576 0.4484
0.750 0.7814 0.00873 0.00245 -0.1671 0.6542 0.4679
1.000 0.8094 0.00873 0.00252 -0.1672 0.6502 0.4884
1.250 0.8373 0.00874 0.00258 -0.1673 0.6461 0.5092
1.500 0.8650 0.00876 0.00265 -0.1673 0.6422 0.5313
1.750 0.8927 0.00878 0.00274 -0.1674 0.6379 0.5537
2.000 0.9201 0.00879 0.00284 -0.1674 0.6330 0.5770
2.250 0.9474 0.00882 0.00293 -0.1673 0.6282 0.6015
2.500 0.9745 0.00885 0.00304 -0.1672 0.6233 0.6264
2.750 1.0014 0.00888 0.00315 -0.1671 0.6173 0.6523
3.000 1.0277 0.00893 0.00325 -0.1669 0.6114 0.6788
3.250 1.0541 0.00895 0.00339 -0.1666 0.6050 0.7075
3.500 1.0798 0.00900 0.00352 -0.1662 0.5983 0.7364
3.750 1.1048 0.00904 0.00365 -0.1657 0.5898 0.7685
4.000 1.1273 0.00911 0.00378 -0.1646 0.5758 0.8028
4.250 1.1474 0.00919 0.00392 -0.1630 0.5588 0.8441
4.500 1.1629 0.00926 0.00404 -0.1603 0.5406 0.9007
4.750 1.1827 0.00939 0.00416 -0.1587 0.5222 1.0000
5.000 1.2046 0.00966 0.00437 -0.1577 0.5050 1.0000
5.250 1.2254 0.00997 0.00460 -0.1565 0.4845 1.0000
5.500 1.2438 0.01036 0.00489 -0.1548 0.4615 1.0000
5.750 1.2621 0.01076 0.00521 -0.1532 0.4394 1.0000
6.000 1.2776 0.01120 0.00556 -0.1510 0.4164 1.0000
6.250 1.2912 0.01168 0.00594 -0.1484 0.3926 1.0000
6.500 1.3029 0.01226 0.00640 -0.1456 0.3673 1.0000
6.750 1.3143 0.01286 0.00691 -0.1429 0.3427 1.0000
7.000 1.3251 0.01353 0.00746 -0.1401 0.3175 1.0000
7.250 1.3341 0.01429 0.00810 -0.1371 0.2913 1.0000
7.500 1.3431 0.01508 0.00879 -0.1342 0.2668 1.0000
7.750 1.3518 0.01593 0.00953 -0.1314 0.2426 1.0000
8.000 1.3587 0.01691 0.01039 -0.1284 0.2173 1.0000
8.250 1.3670 0.01786 0.01126 -0.1258 0.1960 1.0000
8.500 1.3748 0.01890 0.01221 -0.1232 0.1763 1.0000
8.750 1.3826 0.01999 0.01322 -0.1208 0.1564 1.0000
9.000 1.3887 0.02123 0.01437 -0.1182 0.1361 1.0000
9.250 1.3953 0.02252 0.01557 -0.1159 0.1168 1.0000
9.500 1.4018 0.02385 0.01684 -0.1137 0.1000 1.0000
9.750 1.4090 0.02520 0.01813 -0.1117 0.0857 1.0000
10.000 1.4157 0.02664 0.01952 -0.1097 0.0696 1.0000
10.250 1.4197 0.02833 0.02111 -0.1076 0.0541 1.0000
10.500 1.4280 0.02975 0.02252 -0.1059 0.0480 1.0000
10.750 1.4366 0.03118 0.02398 -0.1044 0.0441 1.0000
11.000 1.4451 0.03266 0.02549 -0.1029 0.0405 1.0000
11.250 1.4570 0.03388 0.02679 -0.1018 0.0385 1.0000
11.500 1.4673 0.03527 0.02823 -0.1007 0.0358 1.0000
11.750 1.4752 0.03690 0.02989 -0.0994 0.0329 1.0000
12.000 1.4855 0.03834 0.03139 -0.0983 0.0303 1.0000
12.250 1.4946 0.03993 0.03301 -0.0973 0.0265 1.0000
12.500 1.5023 0.04168 0.03477 -0.0962 0.0224 1.0000
12.750 1.5089 0.04358 0.03669 -0.0952 0.0186 1.0000
13.000 1.5149 0.04560 0.03872 -0.0942 0.0158 1.0000
13.250 1.5211 0.04764 0.04082 -0.0933 0.0139 1.0000
13.500 1.5262 0.04984 0.04306 -0.0924 0.0122 1.0000
13.750 1.5322 0.05200 0.04530 -0.0916 0.0108 1.0000
14.000 1.5359 0.05447 0.04782 -0.0909 0.0096 1.0000
14.250 1.5417 0.05674 0.05017 -0.0903 0.0085 1.0000
14.500 1.5454 0.05930 0.05281 -0.0898 0.0075 1.0000
14.750 1.5495 0.06189 0.05548 -0.0893 0.0068 1.0000
15.000 1.5538 0.06449 0.05817 -0.0890 0.0062 1.0000
15.250 1.5565 0.06736 0.06111 -0.0887 0.0057 1.0000
15.500 1.5581 0.07042 0.06425 -0.0885 0.0052 1.0000
15.750 1.5610 0.07338 0.06732 -0.0885 0.0049 1.0000
16.000 1.5630 0.07652 0.07055 -0.0885 0.0045 1.0000
16.250 1.5640 0.07985 0.07399 -0.0887 0.0042 1.0000
16.500 1.5641 0.08336 0.07758 -0.0890 0.0040 1.0000
16.750 1.5624 0.08722 0.08155 -0.0895 0.0037 1.0000
17.000 1.5621 0.09093 0.08538 -0.0901 0.0035 1.0000
17.250 1.5611 0.09481 0.08938 -0.0908 0.0034 1.0000
17.500 1.5600 0.09877 0.09345 -0.0916 0.0032 1.0000
17.750 1.5578 0.10293 0.09772 -0.0926 0.0030 1.0000
18.000 1.5551 0.10723 0.10214 -0.0938 0.0029 1.0000
18.250 1.5517 0.11171 0.10673 -0.0952 0.0028 1.0000
18.500 1.5474 0.11640 0.11154 -0.0968 0.0027 1.0000
18.750 1.5419 0.12137 0.11662 -0.0987 0.0026 1.0000
19.000 1.5351 0.12661 0.12198 -0.1008 0.0025 1.0000
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Polar data table (+)
Polar graphs
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