EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: EPPLER 395 AIRFOIL (e395-il) Reynolds number: 500,000 Max Cl/Cd: 136.42 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e395-il-500000.txt Download as CSV file: xf-e395-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 395 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2812 0.12665 0.12441 -0.0524 0.9966 0.0173
-11.500 -0.2668 0.12279 0.12055 -0.0559 0.9951 0.0177
-11.250 -0.3946 0.07999 0.07762 -0.0744 0.9918 0.0075
-11.000 -0.4165 0.06800 0.06554 -0.0854 0.9870 0.0073
-10.750 -0.4312 0.05648 0.05385 -0.0985 0.9819 0.0071
-10.500 -0.4411 0.04590 0.04306 -0.1120 0.9722 0.0070
-10.250 -0.4412 0.03643 0.03331 -0.1267 0.9597 0.0070
-10.000 -0.4206 0.02892 0.02534 -0.1423 0.9488 0.0070
-9.750 -0.3885 0.02493 0.02093 -0.1502 0.9452 0.0070
-9.500 -0.3638 0.02257 0.01825 -0.1531 0.9365 0.0072
-9.250 -0.3298 0.02059 0.01600 -0.1569 0.9323 0.0074
-9.000 -0.3032 0.01854 0.01372 -0.1591 0.9239 0.0077
-8.750 -0.2709 0.01710 0.01213 -0.1617 0.9177 0.0083
-8.500 -0.2433 0.01617 0.01106 -0.1626 0.9092 0.0088
-8.250 -0.2123 0.01527 0.00997 -0.1641 0.9024 0.0097
-8.000 -0.1866 0.01427 0.00883 -0.1646 0.8935 0.0106
-7.750 -0.1567 0.01358 0.00800 -0.1656 0.8867 0.0122
-7.500 -0.1308 0.01284 0.00717 -0.1657 0.8784 0.0148
-7.250 -0.1016 0.01220 0.00643 -0.1664 0.8719 0.0212
-7.000 -0.0750 0.01175 0.00598 -0.1666 0.8643 0.0290
-6.750 -0.0464 0.01143 0.00561 -0.1670 0.8579 0.0368
-6.500 -0.0189 0.01113 0.00528 -0.1672 0.8513 0.0446
-6.250 0.0091 0.01085 0.00497 -0.1674 0.8449 0.0532
-6.000 0.0377 0.01061 0.00467 -0.1677 0.8392 0.0625
-5.750 0.0653 0.01038 0.00440 -0.1678 0.8327 0.0720
-5.500 0.0941 0.01017 0.00414 -0.1681 0.8273 0.0829
-5.250 0.1221 0.00992 0.00389 -0.1683 0.8215 0.0961
-5.000 0.1502 0.00971 0.00367 -0.1685 0.8158 0.1104
-4.500 0.2072 0.00935 0.00330 -0.1690 0.8052 0.1426
-4.250 0.2356 0.00920 0.00315 -0.1693 0.7999 0.1595
-4.000 0.2648 0.00909 0.00302 -0.1696 0.7953 0.1776
-3.750 0.2926 0.00897 0.00293 -0.1697 0.7899 0.1965
-3.500 0.3211 0.00888 0.00283 -0.1699 0.7849 0.2150
-3.250 0.3504 0.00881 0.00275 -0.1702 0.7804 0.2343
-3.000 0.3782 0.00872 0.00269 -0.1703 0.7753 0.2534
-2.750 0.4066 0.00865 0.00264 -0.1705 0.7703 0.2731
-2.500 0.4357 0.00863 0.00258 -0.1708 0.7660 0.2928
-2.250 0.4637 0.00856 0.00256 -0.1709 0.7611 0.3121
-2.000 0.4920 0.00850 0.00254 -0.1710 0.7561 0.3321
-1.750 0.5209 0.00848 0.00251 -0.1712 0.7517 0.3528
-1.500 0.5492 0.00845 0.00251 -0.1714 0.7470 0.3737
-1.250 0.5773 0.00840 0.00252 -0.1715 0.7419 0.3958
-0.750 0.6343 0.00837 0.00254 -0.1718 0.7328 0.4439
-0.500 0.6622 0.00834 0.00258 -0.1719 0.7277 0.4697
-0.250 0.6906 0.00832 0.00260 -0.1720 0.7230 0.4972
0.000 0.7191 0.00833 0.00265 -0.1722 0.7185 0.5261
0.250 0.7467 0.00830 0.00272 -0.1722 0.7131 0.5562
0.500 0.7747 0.00828 0.00277 -0.1722 0.7083 0.5875
0.750 0.8030 0.00830 0.00284 -0.1723 0.7036 0.6202
1.250 0.8576 0.00826 0.00300 -0.1721 0.6929 0.6895
1.500 0.8848 0.00828 0.00309 -0.1719 0.6878 0.7272
1.750 0.9108 0.00825 0.00320 -0.1715 0.6817 0.7660
2.000 0.9365 0.00824 0.00327 -0.1709 0.6763 0.8081
2.500 0.9775 0.00809 0.00339 -0.1673 0.6640 0.9212
2.750 1.0049 0.00810 0.00339 -0.1672 0.6579 1.0000
3.000 1.0320 0.00817 0.00347 -0.1671 0.6505 1.0000
3.250 1.0598 0.00829 0.00354 -0.1671 0.6438 1.0000
3.500 1.0863 0.00836 0.00364 -0.1669 0.6358 1.0000
3.750 1.1133 0.00849 0.00372 -0.1668 0.6284 1.0000
4.000 1.1394 0.00858 0.00384 -0.1665 0.6195 1.0000
4.250 1.1656 0.00871 0.00396 -0.1662 0.6111 1.0000
4.500 1.1914 0.00883 0.00408 -0.1658 0.6018 1.0000
4.750 1.2169 0.00896 0.00422 -0.1654 0.5921 1.0000
5.000 1.2420 0.00912 0.00437 -0.1649 0.5818 1.0000
5.250 1.2663 0.00929 0.00453 -0.1643 0.5700 1.0000
5.500 1.2905 0.00946 0.00471 -0.1636 0.5574 1.0000
5.750 1.3139 0.00966 0.00491 -0.1628 0.5436 1.0000
6.000 1.3366 0.00990 0.00513 -0.1618 0.5285 1.0000
6.250 1.3581 0.01017 0.00537 -0.1607 0.5114 1.0000
6.500 1.3788 0.01048 0.00564 -0.1594 0.4930 1.0000
6.750 1.3984 0.01083 0.00594 -0.1579 0.4711 1.0000
7.000 1.4154 0.01127 0.00630 -0.1559 0.4462 1.0000
7.250 1.4300 0.01180 0.00671 -0.1536 0.4165 1.0000
7.500 1.4405 0.01242 0.00719 -0.1504 0.3832 1.0000
7.750 1.4488 0.01313 0.00775 -0.1470 0.3494 1.0000
8.000 1.4564 0.01393 0.00839 -0.1435 0.3163 1.0000
8.250 1.4635 0.01481 0.00911 -0.1401 0.2842 1.0000
8.500 1.4696 0.01577 0.00991 -0.1367 0.2511 1.0000
8.750 1.4750 0.01682 0.01081 -0.1333 0.2196 1.0000
9.000 1.4798 0.01795 0.01178 -0.1300 0.1899 1.0000
9.250 1.4845 0.01916 0.01284 -0.1268 0.1626 1.0000
9.500 1.4893 0.02042 0.01398 -0.1238 0.1389 1.0000
9.750 1.4947 0.02171 0.01517 -0.1211 0.1169 1.0000
10.000 1.4996 0.02309 0.01647 -0.1184 0.0984 1.0000
10.250 1.5051 0.02451 0.01781 -0.1160 0.0814 1.0000
10.500 1.5097 0.02605 0.01929 -0.1136 0.0666 1.0000
10.750 1.5144 0.02765 0.02084 -0.1114 0.0544 1.0000
11.000 1.5187 0.02936 0.02251 -0.1092 0.0440 1.0000
11.250 1.5232 0.03112 0.02426 -0.1073 0.0356 1.0000
11.500 1.5280 0.03291 0.02606 -0.1054 0.0294 1.0000
11.750 1.5326 0.03479 0.02796 -0.1037 0.0245 1.0000
12.000 1.5356 0.03687 0.03008 -0.1020 0.0206 1.0000
12.250 1.5384 0.03905 0.03228 -0.1004 0.0174 1.0000
12.500 1.5430 0.04112 0.03444 -0.0991 0.0150 1.0000
12.750 1.5425 0.04379 0.03714 -0.0976 0.0131 1.0000
13.000 1.5479 0.04590 0.03935 -0.0965 0.0116 1.0000
13.250 1.5486 0.04859 0.04212 -0.0954 0.0105 1.0000
13.500 1.5483 0.05152 0.04516 -0.0944 0.0095 1.0000
13.750 1.5510 0.05417 0.04790 -0.0937 0.0087 1.0000
14.000 1.5513 0.05718 0.05099 -0.0931 0.0080 1.0000
14.250 1.5442 0.06125 0.05516 -0.0925 0.0075 1.0000
14.500 1.5468 0.06417 0.05821 -0.0922 0.0070 1.0000
14.750 1.5476 0.06739 0.06154 -0.0920 0.0065 1.0000
15.000 1.5483 0.07070 0.06494 -0.0920 0.0061 1.0000
15.250 1.5449 0.07469 0.06902 -0.0922 0.0058 1.0000
15.500 1.5327 0.08010 0.07454 -0.0927 0.0055 1.0000
15.750 1.5339 0.08363 0.07822 -0.0931 0.0053 1.0000
16.000 1.5327 0.08759 0.08231 -0.0937 0.0051 1.0000
16.250 1.5305 0.09179 0.08663 -0.0946 0.0048 1.0000
16.500 1.5277 0.09617 0.09113 -0.0956 0.0046 1.0000
16.750 1.5238 0.10079 0.09587 -0.0968 0.0045 1.0000
17.000 1.5192 0.10559 0.10077 -0.0982 0.0043 1.0000
17.250 1.5137 0.11063 0.10592 -0.0999 0.0042 1.0000
17.500 1.5073 0.11589 0.11129 -0.1017 0.0041 1.0000
17.750 1.4999 0.12134 0.11686 -0.1038 0.0040 1.0000
18.000 1.4919 0.12692 0.12255 -0.1061 0.0040 1.0000
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