EPPLER 398 AIRFOIL (e398-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 398 AIRFOIL (e398-il) Reynolds number: 500,000 Max Cl/Cd: 128.99 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e398-il-500000.txt Download as CSV file: xf-e398-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5134 0.07149 0.06885 -0.0789 0.9972 0.0094
-12.250 -0.5332 0.06021 0.05734 -0.0911 0.9932 0.0094
-12.000 -0.5425 0.05126 0.04816 -0.1018 0.9869 0.0091
-11.750 -0.5422 0.04380 0.04049 -0.1122 0.9793 0.0092
-11.500 -0.5344 0.03748 0.03395 -0.1220 0.9699 0.0092
-11.250 -0.5249 0.03214 0.02837 -0.1307 0.9569 0.0093
-11.000 -0.5003 0.02765 0.02361 -0.1409 0.9454 0.0094
-10.750 -0.4731 0.02495 0.02065 -0.1464 0.9349 0.0097
-10.500 -0.4441 0.02289 0.01837 -0.1504 0.9247 0.0100
-10.250 -0.4158 0.02136 0.01659 -0.1530 0.9134 0.0105
-10.000 -0.3950 0.01983 0.01486 -0.1540 0.8996 0.0108
-9.750 -0.3754 0.01855 0.01344 -0.1543 0.8866 0.0113
-9.500 -0.3529 0.01770 0.01247 -0.1545 0.8754 0.0119
-9.250 -0.3294 0.01690 0.01150 -0.1546 0.8652 0.0126
-9.000 -0.3064 0.01609 0.01054 -0.1545 0.8546 0.0135
-8.750 -0.2831 0.01527 0.00962 -0.1546 0.8451 0.0148
-8.500 -0.2580 0.01461 0.00881 -0.1547 0.8365 0.0169
-8.250 -0.2329 0.01404 0.00816 -0.1547 0.8278 0.0199
-8.000 -0.2066 0.01355 0.00757 -0.1548 0.8200 0.0245
-7.750 -0.1811 0.01298 0.00698 -0.1549 0.8116 0.0306
-7.500 -0.1542 0.01260 0.00652 -0.1550 0.8043 0.0365
-7.250 -0.1273 0.01230 0.00617 -0.1550 0.7967 0.0423
-7.000 -0.1002 0.01196 0.00579 -0.1552 0.7898 0.0492
-6.750 -0.0730 0.01164 0.00546 -0.1554 0.7829 0.0568
-6.500 -0.0456 0.01136 0.00514 -0.1555 0.7759 0.0652
-6.250 -0.0178 0.01111 0.00484 -0.1557 0.7696 0.0746
-6.000 0.0099 0.01087 0.00458 -0.1558 0.7629 0.0851
-5.750 0.0380 0.01067 0.00432 -0.1560 0.7571 0.0967
-5.500 0.0659 0.01045 0.00410 -0.1562 0.7510 0.1098
-5.250 0.0939 0.01024 0.00389 -0.1564 0.7449 0.1241
-5.000 0.1224 0.01008 0.00369 -0.1566 0.7395 0.1394
-4.750 0.1505 0.00989 0.00354 -0.1568 0.7338 0.1554
-4.500 0.1788 0.00975 0.00339 -0.1570 0.7283 0.1719
-4.250 0.2074 0.00964 0.00326 -0.1573 0.7233 0.1896
-4.000 0.2357 0.00950 0.00316 -0.1574 0.7178 0.2079
-3.750 0.2641 0.00941 0.00306 -0.1576 0.7127 0.2265
-3.500 0.2930 0.00937 0.00298 -0.1579 0.7082 0.2447
-3.250 0.3213 0.00928 0.00293 -0.1581 0.7031 0.2629
-3.000 0.3498 0.00921 0.00287 -0.1582 0.6982 0.2811
-2.750 0.3786 0.00918 0.00281 -0.1585 0.6938 0.2990
-2.500 0.4071 0.00914 0.00280 -0.1587 0.6894 0.3166
-2.250 0.4355 0.00909 0.00277 -0.1589 0.6847 0.3339
-2.000 0.4641 0.00906 0.00274 -0.1591 0.6802 0.3516
-1.750 0.4930 0.00908 0.00274 -0.1593 0.6762 0.3696
-1.500 0.5213 0.00904 0.00275 -0.1595 0.6718 0.3872
-1.250 0.5498 0.00902 0.00275 -0.1596 0.6674 0.4056
-1.000 0.5784 0.00903 0.00276 -0.1598 0.6634 0.4249
-0.750 0.6071 0.00906 0.00280 -0.1600 0.6595 0.4445
-0.500 0.6353 0.00903 0.00284 -0.1602 0.6552 0.4644
-0.250 0.6637 0.00902 0.00287 -0.1603 0.6510 0.4854
0.000 0.6923 0.00905 0.00291 -0.1605 0.6472 0.5079
0.250 0.7207 0.00907 0.00298 -0.1607 0.6433 0.5306
0.500 0.7487 0.00906 0.00306 -0.1608 0.6391 0.5549
0.750 0.7768 0.00907 0.00312 -0.1609 0.6351 0.5799
1.000 0.8053 0.00911 0.00319 -0.1610 0.6313 0.6063
1.250 0.8333 0.00915 0.00330 -0.1611 0.6274 0.6335
1.500 0.8608 0.00915 0.00340 -0.1611 0.6233 0.6613
1.750 0.8884 0.00917 0.00349 -0.1610 0.6192 0.6909
2.000 0.9161 0.00922 0.00359 -0.1610 0.6154 0.7208
2.250 0.9431 0.00925 0.00372 -0.1608 0.6114 0.7522
2.500 0.9691 0.00925 0.00384 -0.1605 0.6070 0.7855
2.750 0.9946 0.00925 0.00394 -0.1599 0.6029 0.8213
3.000 1.0188 0.00930 0.00404 -0.1590 0.5989 0.8619
3.250 1.0372 0.00921 0.00411 -0.1568 0.5946 0.9191
3.500 1.0644 0.00918 0.00413 -0.1567 0.5898 1.0000
3.750 1.0926 0.00930 0.00422 -0.1569 0.5852 1.0000
4.000 1.1206 0.00945 0.00435 -0.1571 0.5805 1.0000
4.250 1.1475 0.00953 0.00447 -0.1570 0.5751 1.0000
4.500 1.1746 0.00965 0.00456 -0.1570 0.5698 1.0000
4.750 1.2015 0.00978 0.00470 -0.1569 0.5642 1.0000
5.000 1.2276 0.00988 0.00483 -0.1566 0.5581 1.0000
5.250 1.2543 0.01003 0.00496 -0.1565 0.5527 1.0000
5.500 1.2798 0.01014 0.00512 -0.1562 0.5463 1.0000
5.750 1.3051 0.01027 0.00525 -0.1558 0.5392 1.0000
6.000 1.3301 0.01041 0.00542 -0.1553 0.5320 1.0000
6.250 1.3546 0.01054 0.00558 -0.1548 0.5243 1.0000
6.500 1.3788 0.01071 0.00576 -0.1542 0.5165 1.0000
6.750 1.4022 0.01088 0.00594 -0.1535 0.5076 1.0000
7.000 1.4253 0.01105 0.00615 -0.1527 0.4978 1.0000
7.250 1.4473 0.01127 0.00637 -0.1517 0.4880 1.0000
7.500 1.4683 0.01150 0.00661 -0.1505 0.4762 1.0000
7.750 1.4885 0.01175 0.00688 -0.1492 0.4632 1.0000
8.000 1.5066 0.01206 0.00718 -0.1476 0.4479 1.0000
8.250 1.5209 0.01244 0.00752 -0.1452 0.4307 1.0000
8.500 1.5324 0.01289 0.00792 -0.1423 0.4115 1.0000
8.750 1.5420 0.01345 0.00841 -0.1392 0.3885 1.0000
9.000 1.5489 0.01416 0.00903 -0.1357 0.3646 1.0000
9.250 1.5541 0.01499 0.00976 -0.1322 0.3393 1.0000
9.500 1.5581 0.01594 0.01060 -0.1286 0.3136 1.0000
9.750 1.5598 0.01707 0.01162 -0.1249 0.2885 1.0000
10.000 1.5607 0.01833 0.01278 -0.1213 0.2638 1.0000
10.250 1.5609 0.01975 0.01409 -0.1179 0.2396 1.0000
10.500 1.5594 0.02138 0.01562 -0.1146 0.2166 1.0000
10.750 1.5592 0.02306 0.01721 -0.1117 0.1944 1.0000
11.000 1.5577 0.02493 0.01899 -0.1089 0.1744 1.0000
11.250 1.5576 0.02684 0.02083 -0.1064 0.1556 1.0000
11.500 1.5573 0.02886 0.02279 -0.1042 0.1382 1.0000
11.750 1.5563 0.03103 0.02490 -0.1021 0.1221 1.0000
12.000 1.5563 0.03323 0.02705 -0.1002 0.1082 1.0000
12.250 1.5565 0.03549 0.02927 -0.0986 0.0956 1.0000
12.500 1.5565 0.03786 0.03162 -0.0970 0.0837 1.0000
12.750 1.5568 0.04029 0.03403 -0.0957 0.0731 1.0000
13.000 1.5572 0.04279 0.03653 -0.0945 0.0640 1.0000
13.250 1.5572 0.04543 0.03915 -0.0934 0.0559 1.0000
13.500 1.5564 0.04823 0.04194 -0.0924 0.0484 1.0000
13.750 1.5570 0.05097 0.04469 -0.0916 0.0423 1.0000
14.000 1.5579 0.05374 0.04750 -0.0910 0.0370 1.0000
14.250 1.5576 0.05674 0.05051 -0.0904 0.0327 1.0000
14.500 1.5583 0.05968 0.05350 -0.0899 0.0291 1.0000
14.750 1.5588 0.06274 0.05661 -0.0896 0.0261 1.0000
15.000 1.5586 0.06594 0.05986 -0.0894 0.0235 1.0000
15.250 1.5591 0.06913 0.06312 -0.0893 0.0213 1.0000
15.500 1.5593 0.07242 0.06646 -0.0893 0.0193 1.0000
15.750 1.5573 0.07609 0.07020 -0.0895 0.0176 1.0000
16.000 1.5582 0.07942 0.07361 -0.0897 0.0160 1.0000
16.250 1.5536 0.08361 0.07786 -0.0901 0.0147 1.0000
16.500 1.5545 0.08705 0.08140 -0.0905 0.0135 1.0000
16.750 1.5531 0.09088 0.08532 -0.0911 0.0124 1.0000
17.000 1.5471 0.09550 0.09001 -0.0920 0.0115 1.0000
17.250 1.5474 0.09920 0.09382 -0.0928 0.0106 1.0000
17.500 1.5454 0.10330 0.09801 -0.0938 0.0099 1.0000
17.750 1.5386 0.10824 0.10303 -0.0951 0.0093 1.0000
18.000 1.5338 0.11293 0.10784 -0.0965 0.0088 1.0000
18.250 1.5318 0.11718 0.11220 -0.0979 0.0083 1.0000
18.500 1.5289 0.12163 0.11674 -0.0994 0.0078 1.0000
18.750 1.5243 0.12640 0.12161 -0.1012 0.0074 1.0000
19.000 1.5148 0.13207 0.12736 -0.1036 0.0071 1.0000
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