EPPLER 398 AIRFOIL (e398-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 398 AIRFOIL (e398-il) Reynolds number: 1,000,000 Max Cl/Cd: 163.34 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e398-il-1000000.txt Download as CSV file: xf-e398-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.4791 0.11058 0.10864 -0.0584 1.0000 0.0058
-14.500 -0.5094 0.10103 0.09899 -0.0624 1.0000 0.0057
-14.250 -0.5335 0.09329 0.09116 -0.0657 1.0000 0.0056
-14.000 -0.5562 0.08625 0.08406 -0.0686 1.0000 0.0056
-13.750 -0.5731 0.07944 0.07716 -0.0725 0.9997 0.0055
-13.500 -0.5850 0.07103 0.06863 -0.0804 0.9983 0.0054
-13.250 -0.5970 0.06271 0.06018 -0.0889 0.9960 0.0054
-13.000 -0.6057 0.05481 0.05214 -0.0978 0.9931 0.0053
-12.750 -0.6138 0.04724 0.04444 -0.1064 0.9877 0.0054
-12.500 -0.6118 0.03999 0.03702 -0.1167 0.9830 0.0053
-12.250 -0.6178 0.03367 0.03054 -0.1239 0.9667 0.0053
-12.000 -0.6024 0.02760 0.02425 -0.1352 0.9517 0.0053
-11.750 -0.5626 0.02287 0.01923 -0.1492 0.9392 0.0054
-11.500 -0.5329 0.02084 0.01697 -0.1539 0.9218 0.0055
-11.250 -0.5128 0.01947 0.01539 -0.1552 0.9022 0.0056
-11.000 -0.4946 0.01845 0.01418 -0.1553 0.8854 0.0057
-10.750 -0.4760 0.01752 0.01308 -0.1551 0.8712 0.0058
-10.500 -0.4555 0.01673 0.01214 -0.1548 0.8589 0.0059
-10.250 -0.4335 0.01608 0.01135 -0.1546 0.8476 0.0061
-10.000 -0.4143 0.01489 0.00997 -0.1545 0.8363 0.0064
-9.750 -0.3911 0.01416 0.00913 -0.1544 0.8265 0.0068
-9.500 -0.3666 0.01364 0.00850 -0.1544 0.8177 0.0072
-9.250 -0.3413 0.01316 0.00792 -0.1544 0.8089 0.0076
-9.000 -0.3155 0.01276 0.00742 -0.1543 0.8007 0.0081
-8.750 -0.2902 0.01213 0.00670 -0.1544 0.7922 0.0091
-8.500 -0.2639 0.01174 0.00621 -0.1544 0.7845 0.0103
-8.250 -0.2374 0.01126 0.00567 -0.1545 0.7769 0.0125
-8.000 -0.2107 0.01086 0.00521 -0.1546 0.7699 0.0161
-7.750 -0.1835 0.01049 0.00483 -0.1548 0.7627 0.0212
-7.500 -0.1564 0.01023 0.00452 -0.1549 0.7556 0.0260
-7.250 -0.1284 0.00997 0.00425 -0.1551 0.7490 0.0308
-7.000 -0.1008 0.00976 0.00400 -0.1552 0.7424 0.0354
-6.750 -0.0728 0.00952 0.00376 -0.1554 0.7364 0.0415
-6.500 -0.0448 0.00930 0.00353 -0.1556 0.7300 0.0481
-6.250 -0.0170 0.00912 0.00332 -0.1557 0.7239 0.0555
-6.000 0.0115 0.00890 0.00312 -0.1560 0.7181 0.0649
-5.750 0.0397 0.00872 0.00294 -0.1562 0.7123 0.0758
-5.500 0.0679 0.00856 0.00278 -0.1564 0.7070 0.0878
-5.250 0.0966 0.00839 0.00263 -0.1567 0.7016 0.0997
-5.000 0.1249 0.00825 0.00248 -0.1568 0.6960 0.1126
-4.750 0.1534 0.00813 0.00236 -0.1571 0.6910 0.1259
-4.500 0.1823 0.00800 0.00225 -0.1573 0.6861 0.1398
-4.250 0.2108 0.00789 0.00215 -0.1576 0.6811 0.1544
-4.000 0.2392 0.00782 0.00206 -0.1577 0.6762 0.1692
-3.750 0.2682 0.00770 0.00199 -0.1580 0.6717 0.1855
-3.500 0.2970 0.00760 0.00192 -0.1583 0.6671 0.2030
-3.250 0.3254 0.00755 0.00186 -0.1585 0.6625 0.2201
-3.000 0.3543 0.00748 0.00182 -0.1587 0.6584 0.2363
-2.750 0.3832 0.00741 0.00178 -0.1590 0.6540 0.2534
-2.500 0.4119 0.00736 0.00175 -0.1592 0.6497 0.2704
-2.250 0.4403 0.00736 0.00173 -0.1594 0.6453 0.2864
-2.000 0.4693 0.00730 0.00171 -0.1596 0.6416 0.3026
-1.750 0.4982 0.00727 0.00170 -0.1599 0.6375 0.3181
-1.500 0.5267 0.00726 0.00170 -0.1601 0.6335 0.3342
-1.250 0.5551 0.00727 0.00171 -0.1602 0.6293 0.3505
-1.000 0.5841 0.00723 0.00172 -0.1605 0.6258 0.3665
-0.750 0.6129 0.00721 0.00173 -0.1607 0.6220 0.3832
-0.500 0.6413 0.00721 0.00175 -0.1609 0.6180 0.4008
-0.250 0.6695 0.00725 0.00179 -0.1610 0.6139 0.4190
0.000 0.6984 0.00722 0.00182 -0.1612 0.6106 0.4374
0.250 0.7271 0.00721 0.00185 -0.1615 0.6069 0.4569
0.500 0.7555 0.00722 0.00189 -0.1616 0.6030 0.4768
0.750 0.7835 0.00727 0.00195 -0.1617 0.5990 0.4974
1.000 0.8121 0.00725 0.00201 -0.1619 0.5955 0.5193
1.250 0.8407 0.00725 0.00206 -0.1621 0.5918 0.5423
1.500 0.8689 0.00726 0.00213 -0.1623 0.5878 0.5659
1.750 0.8966 0.00732 0.00221 -0.1623 0.5837 0.5908
2.000 0.9249 0.00732 0.00229 -0.1625 0.5801 0.6160
2.500 0.9809 0.00735 0.00246 -0.1626 0.5717 0.6695
2.750 1.0081 0.00742 0.00256 -0.1626 0.5670 0.6969
3.000 1.0361 0.00741 0.00266 -0.1627 0.5631 0.7259
3.250 1.0636 0.00742 0.00275 -0.1626 0.5583 0.7564
3.500 1.0899 0.00747 0.00286 -0.1624 0.5533 0.7889
3.750 1.1164 0.00748 0.00298 -0.1621 0.5484 0.8241
4.000 1.1415 0.00747 0.00308 -0.1615 0.5428 0.8652
4.250 1.1612 0.00746 0.00317 -0.1597 0.5374 0.9245
4.500 1.1871 0.00745 0.00323 -0.1593 0.5323 1.0000
4.750 1.2143 0.00755 0.00333 -0.1593 0.5262 1.0000
5.000 1.2405 0.00770 0.00345 -0.1591 0.5195 1.0000
5.250 1.2676 0.00779 0.00356 -0.1591 0.5121 1.0000
5.500 1.2931 0.00797 0.00370 -0.1587 0.5047 1.0000
5.750 1.3198 0.00808 0.00383 -0.1586 0.4968 1.0000
6.000 1.3448 0.00826 0.00399 -0.1582 0.4881 1.0000
6.250 1.3698 0.00843 0.00415 -0.1578 0.4776 1.0000
6.500 1.3946 0.00861 0.00432 -0.1574 0.4674 1.0000
6.750 1.4181 0.00884 0.00453 -0.1567 0.4551 1.0000
7.000 1.4407 0.00911 0.00475 -0.1558 0.4412 1.0000
7.250 1.4622 0.00941 0.00500 -0.1548 0.4244 1.0000
7.500 1.4817 0.00979 0.00530 -0.1534 0.4036 1.0000
7.750 1.4988 0.01026 0.00567 -0.1516 0.3808 1.0000
8.000 1.5113 0.01081 0.00610 -0.1489 0.3531 1.0000
8.250 1.5212 0.01144 0.00658 -0.1458 0.3245 1.0000
8.500 1.5310 0.01209 0.00711 -0.1427 0.2980 1.0000
8.750 1.5395 0.01280 0.00770 -0.1396 0.2734 1.0000
9.000 1.5461 0.01362 0.00839 -0.1361 0.2477 1.0000
9.250 1.5524 0.01448 0.00913 -0.1328 0.2229 1.0000
9.500 1.5565 0.01548 0.01000 -0.1293 0.1989 1.0000
9.750 1.5600 0.01655 0.01096 -0.1259 0.1763 1.0000
10.000 1.5633 0.01771 0.01202 -0.1227 0.1558 1.0000
10.250 1.5668 0.01894 0.01317 -0.1196 0.1373 1.0000
10.500 1.5697 0.02028 0.01444 -0.1167 0.1208 1.0000
10.750 1.5725 0.02173 0.01581 -0.1140 0.1057 1.0000
11.000 1.5748 0.02329 0.01731 -0.1115 0.0908 1.0000
11.250 1.5785 0.02485 0.01883 -0.1092 0.0796 1.0000
11.500 1.5813 0.02656 0.02049 -0.1071 0.0684 1.0000
12.250 1.5904 0.03209 0.02596 -0.1016 0.0428 1.0000
12.500 1.5947 0.03397 0.02784 -0.1001 0.0371 1.0000
12.750 1.5983 0.03598 0.02985 -0.0988 0.0323 1.0000
13.000 1.6017 0.03808 0.03196 -0.0975 0.0280 1.0000
13.250 1.6071 0.04004 0.03395 -0.0964 0.0250 1.0000
13.500 1.6106 0.04225 0.03619 -0.0954 0.0221 1.0000
13.750 1.6152 0.04442 0.03839 -0.0945 0.0197 1.0000
14.000 1.6192 0.04670 0.04071 -0.0937 0.0177 1.0000
14.250 1.6237 0.04897 0.04303 -0.0930 0.0160 1.0000
14.500 1.6269 0.05146 0.04556 -0.0923 0.0144 1.0000
14.750 1.6313 0.05387 0.04802 -0.0918 0.0131 1.0000
15.000 1.6330 0.05664 0.05082 -0.0913 0.0117 1.0000
15.250 1.6377 0.05910 0.05335 -0.0910 0.0107 1.0000
15.500 1.6396 0.06196 0.05626 -0.0907 0.0097 1.0000
15.750 1.6422 0.06480 0.05916 -0.0905 0.0087 1.0000
16.000 1.6447 0.06771 0.06214 -0.0904 0.0079 1.0000
16.250 1.6445 0.07102 0.06550 -0.0904 0.0071 1.0000
16.500 1.6469 0.07403 0.06859 -0.0905 0.0065 1.0000
16.750 1.6477 0.07731 0.07193 -0.0907 0.0059 1.0000
17.000 1.6458 0.08103 0.07573 -0.0910 0.0054 1.0000
17.250 1.6462 0.08450 0.07928 -0.0914 0.0050 1.0000
17.500 1.6465 0.08801 0.08287 -0.0919 0.0046 1.0000
17.750 1.6446 0.09192 0.08685 -0.0926 0.0043 1.0000
18.000 1.6403 0.09625 0.09127 -0.0935 0.0039 1.0000
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Polar data table (+)
Polar graphs
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