EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 395 AIRFOIL (e395-il) Reynolds number: 1,000,000 Max Cl/Cd: 169.65 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e395-il-1000000.txt Download as CSV file: xf-e395-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4526 0.09296 0.09109 -0.0652 0.9973 0.0040
-12.500 -0.4788 0.08070 0.07868 -0.0745 0.9956 0.0039
-12.250 -0.4862 0.07242 0.07029 -0.0822 0.9941 0.0038
-12.000 -0.4998 0.06375 0.06152 -0.0904 0.9907 0.0038
-11.750 -0.4982 0.05743 0.05512 -0.0976 0.9873 0.0037
-11.500 -0.4979 0.04960 0.04717 -0.1078 0.9840 0.0037
-11.250 -0.5000 0.04306 0.04052 -0.1153 0.9752 0.0037
-11.000 -0.5006 0.03625 0.03357 -0.1240 0.9629 0.0037
-10.750 -0.4784 0.02755 0.02456 -0.1421 0.9510 0.0036
-10.500 -0.4418 0.02265 0.01928 -0.1543 0.9444 0.0036
-10.250 -0.4121 0.01991 0.01624 -0.1595 0.9336 0.0037
-10.000 -0.3847 0.01794 0.01401 -0.1624 0.9215 0.0037
-9.750 -0.3602 0.01634 0.01217 -0.1640 0.9087 0.0038
-9.500 -0.3365 0.01503 0.01063 -0.1648 0.8968 0.0039
-9.250 -0.3115 0.01416 0.00959 -0.1652 0.8863 0.0040
-9.000 -0.2867 0.01343 0.00872 -0.1654 0.8762 0.0042
-8.750 -0.2609 0.01282 0.00798 -0.1656 0.8674 0.0044
-8.500 -0.2348 0.01229 0.00733 -0.1657 0.8586 0.0046
-8.250 -0.2083 0.01179 0.00672 -0.1659 0.8509 0.0049
-8.000 -0.1814 0.01140 0.00622 -0.1660 0.8431 0.0053
-7.750 -0.1547 0.01077 0.00548 -0.1662 0.8358 0.0063
-7.500 -0.1274 0.01043 0.00504 -0.1663 0.8287 0.0074
-7.250 -0.1000 0.00989 0.00445 -0.1666 0.8223 0.0116
-7.000 -0.0725 0.00950 0.00405 -0.1668 0.8156 0.0186
-6.750 -0.0447 0.00925 0.00377 -0.1670 0.8097 0.0247
-6.500 -0.0166 0.00900 0.00352 -0.1672 0.8037 0.0302
-6.250 0.0113 0.00880 0.00328 -0.1674 0.7978 0.0361
-6.000 0.0396 0.00861 0.00307 -0.1676 0.7924 0.0424
-5.750 0.0678 0.00841 0.00288 -0.1678 0.7867 0.0508
-5.500 0.0960 0.00824 0.00270 -0.1680 0.7814 0.0617
-5.250 0.1245 0.00803 0.00253 -0.1683 0.7765 0.0751
-5.000 0.1529 0.00786 0.00238 -0.1685 0.7712 0.0886
-4.750 0.1813 0.00774 0.00225 -0.1687 0.7662 0.1017
-4.500 0.2100 0.00759 0.00212 -0.1690 0.7615 0.1157
-4.250 0.2386 0.00747 0.00201 -0.1692 0.7566 0.1298
-4.000 0.2670 0.00737 0.00191 -0.1694 0.7519 0.1452
-3.750 0.2957 0.00727 0.00182 -0.1696 0.7474 0.1605
-3.500 0.3244 0.00716 0.00175 -0.1699 0.7427 0.1769
-3.250 0.3530 0.00709 0.00169 -0.1701 0.7381 0.1948
-3.000 0.3816 0.00703 0.00163 -0.1703 0.7337 0.2114
-2.750 0.4103 0.00695 0.00159 -0.1705 0.7292 0.2288
-2.500 0.4389 0.00690 0.00155 -0.1707 0.7246 0.2455
-2.250 0.4673 0.00688 0.00152 -0.1708 0.7201 0.2634
-2.000 0.4961 0.00681 0.00150 -0.1711 0.7159 0.2811
-1.750 0.5247 0.00676 0.00149 -0.1713 0.7112 0.2991
-1.500 0.5530 0.00675 0.00148 -0.1714 0.7067 0.3167
-1.250 0.5816 0.00672 0.00148 -0.1716 0.7024 0.3357
-1.000 0.6102 0.00669 0.00148 -0.1718 0.6977 0.3545
-0.750 0.6385 0.00667 0.00149 -0.1719 0.6931 0.3742
-0.500 0.6669 0.00667 0.00151 -0.1721 0.6886 0.3947
-0.250 0.6954 0.00663 0.00154 -0.1723 0.6840 0.4174
0.000 0.7237 0.00661 0.00157 -0.1724 0.6791 0.4412
0.250 0.7518 0.00664 0.00161 -0.1725 0.6743 0.4652
0.500 0.7803 0.00660 0.00165 -0.1727 0.6694 0.4912
0.750 0.8084 0.00659 0.00170 -0.1728 0.6641 0.5176
1.000 0.8362 0.00662 0.00175 -0.1728 0.6588 0.5457
1.250 0.8645 0.00659 0.00181 -0.1729 0.6532 0.5747
1.500 0.8922 0.00660 0.00188 -0.1729 0.6473 0.6050
1.750 0.9199 0.00661 0.00196 -0.1730 0.6415 0.6360
2.000 0.9476 0.00661 0.00203 -0.1730 0.6347 0.6688
2.250 0.9747 0.00664 0.00212 -0.1728 0.6281 0.7029
2.500 1.0021 0.00663 0.00222 -0.1728 0.6207 0.7389
2.750 1.0284 0.00667 0.00232 -0.1725 0.6134 0.7770
3.000 1.0547 0.00666 0.00242 -0.1721 0.6054 0.8180
3.250 1.0789 0.00668 0.00254 -0.1713 0.5973 0.8656
3.500 1.0974 0.00660 0.00260 -0.1691 0.5887 0.9401
3.750 1.1240 0.00666 0.00266 -0.1689 0.5799 1.0000
4.000 1.1503 0.00681 0.00277 -0.1687 0.5699 1.0000
4.250 1.1769 0.00694 0.00289 -0.1685 0.5593 1.0000
4.500 1.2028 0.00709 0.00301 -0.1682 0.5476 1.0000
4.750 1.2282 0.00728 0.00316 -0.1678 0.5348 1.0000
5.000 1.2531 0.00748 0.00332 -0.1673 0.5205 1.0000
5.250 1.2775 0.00770 0.00349 -0.1667 0.5051 1.0000
5.500 1.3014 0.00794 0.00369 -0.1660 0.4875 1.0000
5.750 1.3241 0.00824 0.00391 -0.1651 0.4674 1.0000
6.000 1.3463 0.00857 0.00416 -0.1641 0.4460 1.0000
6.250 1.3668 0.00897 0.00445 -0.1629 0.4199 1.0000
6.500 1.3857 0.00945 0.00480 -0.1613 0.3894 1.0000
6.750 1.4022 0.01005 0.00521 -0.1594 0.3511 1.0000
7.000 1.4166 0.01073 0.00569 -0.1571 0.3132 1.0000
7.250 1.4308 0.01132 0.00613 -0.1547 0.2825 1.0000
7.500 1.4423 0.01197 0.00663 -0.1518 0.2512 1.0000
7.750 1.4524 0.01269 0.00718 -0.1487 0.2195 1.0000
8.000 1.4612 0.01349 0.00780 -0.1455 0.1876 1.0000
8.250 1.4706 0.01428 0.00845 -0.1425 0.1604 1.0000
8.500 1.4802 0.01507 0.00912 -0.1396 0.1378 1.0000
8.750 1.4893 0.01591 0.00984 -0.1367 0.1160 1.0000
9.000 1.4982 0.01679 0.01062 -0.1338 0.0971 1.0000
9.250 1.5072 0.01770 0.01146 -0.1311 0.0805 1.0000
9.500 1.5155 0.01868 0.01236 -0.1284 0.0662 1.0000
9.750 1.5241 0.01968 0.01331 -0.1259 0.0544 1.0000
10.000 1.5327 0.02074 0.01432 -0.1235 0.0443 1.0000
10.250 1.5408 0.02187 0.01541 -0.1211 0.0354 1.0000
10.500 1.5492 0.02302 0.01654 -0.1189 0.0285 1.0000
10.750 1.5579 0.02422 0.01773 -0.1168 0.0232 1.0000
11.000 1.5664 0.02546 0.01898 -0.1148 0.0187 1.0000
11.250 1.5752 0.02673 0.02026 -0.1130 0.0156 1.0000
11.500 1.5830 0.02812 0.02168 -0.1111 0.0129 1.0000
11.750 1.5913 0.02951 0.02309 -0.1094 0.0108 1.0000
12.000 1.5996 0.03095 0.02457 -0.1078 0.0091 1.0000
12.250 1.6056 0.03263 0.02628 -0.1061 0.0076 1.0000
12.500 1.6143 0.03413 0.02785 -0.1047 0.0067 1.0000
12.750 1.6199 0.03594 0.02971 -0.1032 0.0058 1.0000
13.000 1.6267 0.03771 0.03154 -0.1019 0.0051 1.0000
13.250 1.6334 0.03952 0.03341 -0.1007 0.0047 1.0000
13.500 1.6362 0.04178 0.03574 -0.0993 0.0040 1.0000
13.750 1.6406 0.04395 0.03799 -0.0982 0.0037 1.0000
14.000 1.6463 0.04604 0.04016 -0.0972 0.0034 1.0000
14.250 1.6509 0.04829 0.04249 -0.0963 0.0032 1.0000
14.500 1.6544 0.05075 0.04502 -0.0955 0.0030 1.0000
14.750 1.6533 0.05381 0.04818 -0.0947 0.0027 1.0000
15.000 1.6510 0.05714 0.05162 -0.0940 0.0025 1.0000
15.250 1.6539 0.05989 0.05447 -0.0936 0.0025 1.0000
15.500 1.6560 0.06283 0.05750 -0.0933 0.0024 1.0000
15.750 1.6567 0.06602 0.06079 -0.0931 0.0023 1.0000
16.000 1.6567 0.06938 0.06424 -0.0931 0.0022 1.0000
16.250 1.6560 0.07293 0.06789 -0.0932 0.0021 1.0000
16.500 1.6547 0.07664 0.07171 -0.0935 0.0020 1.0000
16.750 1.6529 0.08052 0.07569 -0.0939 0.0020 1.0000
17.000 1.6496 0.08470 0.07997 -0.0946 0.0019 1.0000
17.250 1.6458 0.08907 0.08446 -0.0954 0.0019 1.0000
17.500 1.6405 0.09377 0.08928 -0.0965 0.0018 1.0000
17.750 1.6341 0.09877 0.09439 -0.0978 0.0018 1.0000
18.000 1.6264 0.10407 0.09980 -0.0994 0.0017 1.0000
18.250 1.6167 0.10983 0.10569 -0.1013 0.0017 1.0000
18.500 1.6056 0.11596 0.11195 -0.1036 0.0016 1.0000
18.750 1.5931 0.12247 0.11860 -0.1063 0.0016 1.0000
19.000 1.5791 0.12935 0.12562 -0.1094 0.0016 1.0000
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