EPPLER 398 AIRFOIL (e398-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 398 AIRFOIL (e398-il) Reynolds number: 500,000 Max Cl/Cd: 124.82 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e398-il-500000-n5.txt Download as CSV file: xf-e398-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 398 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.4301 0.12079 0.11823 -0.0555 1.0000 0.0055
-14.500 -0.4586 0.11106 0.10841 -0.0592 1.0000 0.0054
-14.250 -0.4783 0.10374 0.10102 -0.0620 1.0000 0.0053
-14.000 -0.4959 0.09592 0.09312 -0.0662 0.9995 0.0054
-13.750 -0.5055 0.08807 0.08517 -0.0723 0.9980 0.0053
-13.500 -0.5177 0.07989 0.07690 -0.0790 0.9955 0.0053
-13.250 -0.5326 0.07183 0.06873 -0.0857 0.9915 0.0053
-13.000 -0.5481 0.06393 0.06071 -0.0927 0.9858 0.0051
-12.500 -0.5825 0.04869 0.04521 -0.1062 0.9594 0.0051
-12.250 -0.5850 0.04047 0.03678 -0.1173 0.9449 0.0053
-12.000 -0.5663 0.03272 0.02875 -0.1321 0.9318 0.0052
-11.750 -0.5433 0.02693 0.02264 -0.1449 0.9111 0.0054
-11.500 -0.5270 0.02423 0.01965 -0.1499 0.8893 0.0055
-11.250 -0.5125 0.02266 0.01786 -0.1510 0.8724 0.0057
-11.000 -0.4962 0.02147 0.01647 -0.1513 0.8589 0.0058
-10.750 -0.4783 0.02041 0.01522 -0.1514 0.8473 0.0060
-10.500 -0.4593 0.01942 0.01406 -0.1514 0.8361 0.0062
-10.250 -0.4395 0.01843 0.01293 -0.1514 0.8257 0.0065
-10.000 -0.4174 0.01770 0.01205 -0.1514 0.8164 0.0068
-9.750 -0.3945 0.01700 0.01122 -0.1514 0.8073 0.0072
-9.500 -0.3706 0.01638 0.01046 -0.1514 0.7995 0.0077
-9.250 -0.3462 0.01582 0.00977 -0.1514 0.7913 0.0082
-9.000 -0.3217 0.01520 0.00905 -0.1515 0.7836 0.0090
-8.750 -0.2964 0.01471 0.00844 -0.1515 0.7757 0.0100
-8.500 -0.2708 0.01421 0.00785 -0.1516 0.7688 0.0116
-8.250 -0.2446 0.01376 0.00733 -0.1517 0.7618 0.0137
-8.000 -0.2184 0.01336 0.00685 -0.1518 0.7553 0.0168
-7.750 -0.1916 0.01297 0.00642 -0.1520 0.7485 0.0205
-7.500 -0.1648 0.01264 0.00602 -0.1521 0.7419 0.0244
-7.250 -0.1376 0.01232 0.00565 -0.1522 0.7358 0.0286
-7.000 -0.1103 0.01201 0.00531 -0.1524 0.7297 0.0337
-6.500 -0.0552 0.01146 0.00471 -0.1528 0.7182 0.0467
-6.250 -0.0275 0.01122 0.00444 -0.1529 0.7123 0.0541
-6.000 0.0002 0.01101 0.00418 -0.1531 0.7070 0.0621
-5.750 0.0284 0.01080 0.00395 -0.1533 0.7018 0.0707
-5.500 0.0564 0.01059 0.00373 -0.1535 0.6964 0.0807
-5.250 0.0844 0.01041 0.00353 -0.1537 0.6915 0.0911
-5.000 0.1128 0.01024 0.00335 -0.1539 0.6863 0.1017
-4.750 0.1411 0.01009 0.00319 -0.1541 0.6813 0.1132
-4.000 0.2262 0.00971 0.00279 -0.1547 0.6674 0.1536
-3.750 0.2545 0.00961 0.00268 -0.1549 0.6629 0.1689
-3.500 0.2830 0.00952 0.00259 -0.1551 0.6589 0.1838
-3.250 0.3117 0.00942 0.00251 -0.1554 0.6545 0.1996
-2.750 0.3684 0.00930 0.00238 -0.1557 0.6459 0.2320
-2.250 0.4256 0.00918 0.00231 -0.1562 0.6379 0.2636
-2.000 0.4540 0.00915 0.00228 -0.1563 0.6337 0.2796
-1.500 0.5109 0.00910 0.00225 -0.1567 0.6261 0.3108
-1.250 0.5394 0.00907 0.00225 -0.1569 0.6221 0.3264
-1.000 0.5677 0.00907 0.00226 -0.1570 0.6181 0.3424
-0.750 0.5959 0.00908 0.00227 -0.1571 0.6144 0.3584
-0.500 0.6244 0.00906 0.00229 -0.1573 0.6108 0.3744
-0.250 0.6528 0.00906 0.00233 -0.1575 0.6068 0.3909
0.000 0.6809 0.00907 0.00236 -0.1576 0.6029 0.4080
0.250 0.7089 0.00910 0.00240 -0.1577 0.5993 0.4254
0.500 0.7372 0.00911 0.00246 -0.1578 0.5957 0.4435
0.750 0.7654 0.00911 0.00252 -0.1580 0.5918 0.4622
1.000 0.7934 0.00913 0.00259 -0.1581 0.5878 0.4818
1.250 0.8212 0.00917 0.00266 -0.1581 0.5841 0.5029
1.500 0.8492 0.00920 0.00275 -0.1582 0.5805 0.5242
1.750 0.8771 0.00922 0.00284 -0.1583 0.5764 0.5467
2.000 0.9048 0.00925 0.00293 -0.1583 0.5723 0.5693
2.250 0.9321 0.00931 0.00303 -0.1583 0.5684 0.5930
2.500 0.9597 0.00934 0.00315 -0.1583 0.5644 0.6171
2.750 0.9872 0.00938 0.00327 -0.1583 0.5600 0.6423
3.000 1.0141 0.00943 0.00339 -0.1582 0.5554 0.6683
3.250 1.0407 0.00950 0.00352 -0.1580 0.5511 0.6954
3.500 1.0676 0.00953 0.00366 -0.1579 0.5462 0.7245
3.750 1.0936 0.00957 0.00381 -0.1576 0.5408 0.7557
4.000 1.1185 0.00965 0.00395 -0.1570 0.5357 0.7889
4.250 1.1432 0.00966 0.00410 -0.1564 0.5299 0.8259
4.500 1.1645 0.00968 0.00423 -0.1550 0.5235 0.8722
4.750 1.1846 0.00962 0.00429 -0.1532 0.5171 1.0000
5.000 1.2105 0.00977 0.00444 -0.1530 0.5095 1.0000
5.250 1.2359 0.00994 0.00460 -0.1526 0.5026 1.0000
5.500 1.2612 0.01011 0.00478 -0.1523 0.4942 1.0000
5.750 1.2856 0.01030 0.00496 -0.1518 0.4851 1.0000
6.000 1.3086 0.01054 0.00517 -0.1510 0.4743 1.0000
6.250 1.3321 0.01075 0.00539 -0.1503 0.4628 1.0000
6.500 1.3545 0.01101 0.00563 -0.1494 0.4505 1.0000
6.750 1.3756 0.01130 0.00590 -0.1483 0.4370 1.0000
7.000 1.3949 0.01165 0.00621 -0.1469 0.4206 1.0000
7.250 1.4120 0.01204 0.00655 -0.1451 0.4030 1.0000
7.500 1.4260 0.01250 0.00693 -0.1427 0.3846 1.0000
7.750 1.4383 0.01303 0.00739 -0.1401 0.3634 1.0000
8.000 1.4490 0.01365 0.00792 -0.1372 0.3407 1.0000
8.250 1.4573 0.01440 0.00856 -0.1341 0.3157 1.0000
8.500 1.4628 0.01530 0.00933 -0.1307 0.2887 1.0000
8.750 1.4679 0.01628 0.01019 -0.1274 0.2633 1.0000
9.000 1.4721 0.01735 0.01115 -0.1241 0.2382 1.0000
9.250 1.4751 0.01856 0.01224 -0.1208 0.2145 1.0000
9.500 1.4783 0.01984 0.01343 -0.1178 0.1922 1.0000
10.000 1.4865 0.02255 0.01601 -0.1126 0.1570 1.0000
10.250 1.4907 0.02402 0.01742 -0.1103 0.1409 1.0000
10.500 1.4948 0.02557 0.01894 -0.1081 0.1263 1.0000
10.750 1.4991 0.02720 0.02053 -0.1061 0.1137 1.0000
11.000 1.5025 0.02896 0.02226 -0.1041 0.1009 1.0000
11.250 1.5059 0.03079 0.02407 -0.1024 0.0895 1.0000
11.500 1.5086 0.03275 0.02600 -0.1007 0.0784 1.0000
11.750 1.5112 0.03479 0.02801 -0.0991 0.0684 1.0000
12.000 1.5147 0.03682 0.03004 -0.0978 0.0599 1.0000
12.250 1.5190 0.03885 0.03208 -0.0966 0.0530 1.0000
12.500 1.5220 0.04106 0.03429 -0.0954 0.0464 1.0000
12.750 1.5246 0.04338 0.03663 -0.0943 0.0404 1.0000
13.000 1.5288 0.04561 0.03888 -0.0935 0.0356 1.0000
13.250 1.5324 0.04795 0.04126 -0.0926 0.0317 1.0000
13.500 1.5353 0.05042 0.04376 -0.0919 0.0280 1.0000
13.750 1.5397 0.05281 0.04620 -0.0913 0.0251 1.0000
14.000 1.5420 0.05549 0.04891 -0.0908 0.0222 1.0000
14.250 1.5456 0.05806 0.05154 -0.0903 0.0198 1.0000
14.500 1.5483 0.06079 0.05432 -0.0900 0.0177 1.0000
14.750 1.5514 0.06354 0.05713 -0.0898 0.0159 1.0000
15.000 1.5533 0.06650 0.06014 -0.0896 0.0143 1.0000
15.250 1.5564 0.06934 0.06306 -0.0895 0.0129 1.0000
15.750 1.5602 0.07552 0.06938 -0.0896 0.0106 1.0000
16.000 1.5618 0.07872 0.07265 -0.0898 0.0097 1.0000
16.250 1.5626 0.08211 0.07611 -0.0901 0.0089 1.0000
16.500 1.5640 0.08544 0.07954 -0.0905 0.0081 1.0000
16.750 1.5644 0.08894 0.08312 -0.0910 0.0074 1.0000
17.000 1.5641 0.09264 0.08690 -0.0917 0.0068 1.0000
17.250 1.5643 0.09629 0.09065 -0.0924 0.0062 1.0000
17.500 1.5639 0.10006 0.09451 -0.0932 0.0058 1.0000
17.750 1.5621 0.10411 0.09864 -0.0942 0.0054 1.0000
18.000 1.5608 0.10811 0.10274 -0.0952 0.0050 1.0000
18.250 1.5598 0.11208 0.10682 -0.0964 0.0047 1.0000
18.500 1.5580 0.11624 0.11108 -0.0977 0.0045 1.0000
18.750 1.5555 0.12055 0.11549 -0.0992 0.0042 1.0000
19.000 1.5525 0.12497 0.12001 -0.1008 0.0040 1.0000
19.250 1.5487 0.12952 0.12466 -0.1026 0.0038 1.0000
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