EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 395 AIRFOIL (e395-il) Reynolds number: 500,000 Max Cl/Cd: 128.5 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e395-il-500000-n5.txt Download as CSV file: xf-e395-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4322 0.08757 0.08485 -0.0737 0.9925 0.0036
-12.250 -0.4443 0.07953 0.07674 -0.0799 0.9892 0.0035
-12.000 -0.4619 0.07013 0.06724 -0.0880 0.9851 0.0035
-11.750 -0.4800 0.06192 0.05895 -0.0949 0.9773 0.0034
-11.500 -0.5004 0.05360 0.05052 -0.1021 0.9641 0.0034
-11.250 -0.5201 0.04416 0.04092 -0.1119 0.9487 0.0033
-11.000 -0.5169 0.03246 0.02889 -0.1309 0.9348 0.0033
-10.750 -0.4834 0.02572 0.02171 -0.1471 0.9247 0.0033
-10.250 -0.4253 0.02138 0.01684 -0.1558 0.9055 0.0036
-10.000 -0.3998 0.01980 0.01503 -0.1580 0.8953 0.0037
-9.750 -0.3743 0.01845 0.01347 -0.1595 0.8857 0.0039
-9.500 -0.3497 0.01749 0.01234 -0.1602 0.8758 0.0042
-9.250 -0.3241 0.01667 0.01135 -0.1608 0.8673 0.0044
-9.000 -0.2984 0.01595 0.01047 -0.1613 0.8590 0.0047
-8.750 -0.2725 0.01529 0.00966 -0.1616 0.8512 0.0050
-8.500 -0.2462 0.01471 0.00892 -0.1619 0.8434 0.0053
-8.250 -0.2200 0.01405 0.00814 -0.1622 0.8363 0.0059
-8.000 -0.1933 0.01354 0.00751 -0.1624 0.8293 0.0067
-7.750 -0.1663 0.01306 0.00691 -0.1627 0.8229 0.0078
-7.500 -0.1393 0.01261 0.00638 -0.1629 0.8162 0.0097
-7.250 -0.1119 0.01220 0.00588 -0.1632 0.8104 0.0130
-7.000 -0.0846 0.01179 0.00545 -0.1634 0.8043 0.0178
-6.750 -0.0570 0.01145 0.00508 -0.1637 0.7984 0.0235
-6.500 -0.0292 0.01115 0.00475 -0.1639 0.7930 0.0298
-6.250 -0.0014 0.01087 0.00445 -0.1642 0.7873 0.0374
-6.000 0.0266 0.01062 0.00416 -0.1644 0.7820 0.0453
-5.750 0.0547 0.01038 0.00390 -0.1646 0.7769 0.0531
-5.500 0.0829 0.01017 0.00366 -0.1648 0.7715 0.0611
-5.250 0.1111 0.00999 0.00344 -0.1650 0.7666 0.0702
-5.000 0.1394 0.00979 0.00324 -0.1653 0.7617 0.0813
-4.750 0.1677 0.00962 0.00305 -0.1655 0.7566 0.0925
-4.500 0.1961 0.00947 0.00288 -0.1657 0.7519 0.1043
-4.250 0.2245 0.00934 0.00273 -0.1659 0.7473 0.1166
-4.000 0.2529 0.00921 0.00260 -0.1661 0.7425 0.1297
-3.750 0.2813 0.00909 0.00248 -0.1663 0.7378 0.1451
-3.500 0.3098 0.00899 0.00238 -0.1665 0.7335 0.1601
-3.250 0.3382 0.00889 0.00230 -0.1667 0.7287 0.1756
-3.000 0.3666 0.00881 0.00222 -0.1669 0.7240 0.1916
-2.500 0.4235 0.00867 0.00210 -0.1673 0.7153 0.2250
-2.250 0.4519 0.00862 0.00206 -0.1674 0.7106 0.2417
-2.000 0.4802 0.00859 0.00202 -0.1676 0.7062 0.2579
-1.750 0.5086 0.00854 0.00200 -0.1678 0.7019 0.2749
-1.500 0.5370 0.00851 0.00199 -0.1679 0.6971 0.2917
-1.000 0.5934 0.00847 0.00198 -0.1682 0.6882 0.3262
-0.750 0.6217 0.00844 0.00199 -0.1683 0.6833 0.3448
-0.500 0.6498 0.00843 0.00201 -0.1684 0.6783 0.3641
-0.250 0.6778 0.00843 0.00203 -0.1685 0.6739 0.3835
0.000 0.7060 0.00842 0.00207 -0.1686 0.6688 0.4041
0.250 0.7339 0.00841 0.00212 -0.1687 0.6637 0.4258
0.500 0.7618 0.00843 0.00216 -0.1687 0.6590 0.4482
0.750 0.7898 0.00842 0.00223 -0.1688 0.6537 0.4714
1.000 0.8175 0.00843 0.00230 -0.1688 0.6481 0.4962
1.250 0.8451 0.00846 0.00237 -0.1688 0.6429 0.5222
1.500 0.8728 0.00846 0.00246 -0.1688 0.6368 0.5495
1.750 0.8999 0.00849 0.00255 -0.1687 0.6307 0.5778
2.000 0.9273 0.00851 0.00265 -0.1687 0.6242 0.6072
2.250 0.9541 0.00855 0.00275 -0.1685 0.6171 0.6375
2.500 0.9809 0.00858 0.00288 -0.1683 0.6100 0.6694
2.750 1.0071 0.00862 0.00300 -0.1680 0.6019 0.7026
3.000 1.0330 0.00866 0.00313 -0.1676 0.5933 0.7380
3.250 1.0578 0.00873 0.00327 -0.1670 0.5842 0.7764
3.500 1.0818 0.00875 0.00341 -0.1662 0.5742 0.8189
3.750 1.1026 0.00877 0.00354 -0.1646 0.5644 0.8724
4.000 1.1216 0.00875 0.00359 -0.1626 0.5536 1.0000
4.250 1.1469 0.00893 0.00375 -0.1621 0.5413 1.0000
4.500 1.1719 0.00912 0.00392 -0.1617 0.5287 1.0000
4.750 1.1963 0.00934 0.00410 -0.1611 0.5151 1.0000
5.000 1.2199 0.00959 0.00431 -0.1603 0.5001 1.0000
5.250 1.2423 0.00988 0.00454 -0.1594 0.4823 1.0000
5.500 1.2639 0.01020 0.00480 -0.1583 0.4637 1.0000
5.750 1.2849 0.01055 0.00509 -0.1571 0.4420 1.0000
6.000 1.3040 0.01098 0.00542 -0.1556 0.4184 1.0000
6.250 1.3218 0.01146 0.00579 -0.1539 0.3914 1.0000
6.500 1.3378 0.01201 0.00622 -0.1518 0.3624 1.0000
6.750 1.3511 0.01260 0.00667 -0.1493 0.3331 1.0000
7.000 1.3627 0.01326 0.00720 -0.1465 0.3029 1.0000
7.250 1.3732 0.01400 0.00779 -0.1436 0.2719 1.0000
7.500 1.3831 0.01479 0.00843 -0.1406 0.2419 1.0000
8.000 1.4008 0.01656 0.00990 -0.1348 0.1837 1.0000
8.250 1.4111 0.01741 0.01066 -0.1322 0.1616 1.0000
8.500 1.4206 0.01832 0.01148 -0.1296 0.1414 1.0000
8.750 1.4302 0.01927 0.01235 -0.1271 0.1231 1.0000
9.000 1.4385 0.02032 0.01332 -0.1245 0.1041 1.0000
9.250 1.4458 0.02149 0.01440 -0.1220 0.0869 1.0000
9.500 1.4541 0.02264 0.01550 -0.1197 0.0725 1.0000
9.750 1.4623 0.02384 0.01667 -0.1175 0.0602 1.0000
10.000 1.4706 0.02509 0.01789 -0.1154 0.0503 1.0000
10.250 1.4787 0.02640 0.01918 -0.1134 0.0417 1.0000
10.750 1.4951 0.02914 0.02192 -0.1097 0.0288 1.0000
11.000 1.5034 0.03057 0.02338 -0.1081 0.0242 1.0000
11.250 1.5110 0.03210 0.02494 -0.1064 0.0203 1.0000
11.500 1.5182 0.03371 0.02658 -0.1049 0.0172 1.0000
11.750 1.5261 0.03531 0.02822 -0.1035 0.0148 1.0000
12.000 1.5328 0.03705 0.03001 -0.1021 0.0128 1.0000
12.250 1.5398 0.03881 0.03183 -0.1008 0.0110 1.0000
12.500 1.5461 0.04069 0.03377 -0.0996 0.0096 1.0000
12.750 1.5524 0.04263 0.03577 -0.0985 0.0083 1.0000
13.000 1.5576 0.04473 0.03794 -0.0974 0.0073 1.0000
13.250 1.5636 0.04680 0.04010 -0.0964 0.0065 1.0000
13.500 1.5679 0.04911 0.04248 -0.0955 0.0058 1.0000
13.750 1.5720 0.05151 0.04496 -0.0947 0.0053 1.0000
14.000 1.5763 0.05393 0.04749 -0.0940 0.0049 1.0000
14.250 1.5797 0.05653 0.05018 -0.0934 0.0045 1.0000
14.500 1.5819 0.05934 0.05308 -0.0929 0.0041 1.0000
14.750 1.5827 0.06240 0.05623 -0.0925 0.0038 1.0000
15.000 1.5853 0.06531 0.05926 -0.0923 0.0036 1.0000
15.250 1.5867 0.06843 0.06250 -0.0922 0.0033 1.0000
15.500 1.5877 0.07169 0.06587 -0.0922 0.0031 1.0000
15.750 1.5877 0.07518 0.06946 -0.0924 0.0029 1.0000
16.000 1.5865 0.07892 0.07331 -0.0927 0.0028 1.0000
16.250 1.5828 0.08311 0.07761 -0.0932 0.0026 1.0000
16.500 1.5810 0.08710 0.08172 -0.0939 0.0025 1.0000
16.750 1.5792 0.09119 0.08594 -0.0947 0.0024 1.0000
17.000 1.5764 0.09550 0.09038 -0.0956 0.0023 1.0000
17.250 1.5729 0.10000 0.09501 -0.0968 0.0022 1.0000
17.500 1.5687 0.10469 0.09983 -0.0982 0.0021 1.0000
17.750 1.5641 0.10951 0.10477 -0.0998 0.0020 1.0000
18.000 1.5590 0.11451 0.10990 -0.1016 0.0019 1.0000
18.250 1.5531 0.11971 0.11524 -0.1036 0.0019 1.0000
18.500 1.5469 0.12503 0.12069 -0.1059 0.0018 1.0000
18.750 1.5396 0.13062 0.12641 -0.1084 0.0018 1.0000
19.000 1.5323 0.13628 0.13221 -0.1111 0.0017 1.0000
19.250 1.5245 0.14211 0.13817 -0.1141 0.0017 1.0000
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Polar data table (+)
Polar graphs
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