EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 395 AIRFOIL (e395-il) Reynolds number: 1,000,000 Max Cl/Cd: 144.11 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e395-il-1000000-n5.txt Download as CSV file: xf-e395-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.4691 0.08554 0.08329 -0.0806 0.9918 0.0020
-13.000 -0.4885 0.07679 0.07446 -0.0870 0.9891 0.0020
-12.750 -0.5100 0.06764 0.06523 -0.0948 0.9857 0.0020
-12.500 -0.5431 0.05745 0.05493 -0.1031 0.9785 0.0020
-12.000 -0.5928 0.03056 0.02751 -0.1368 0.9422 0.0019
-11.750 -0.5520 0.02331 0.01982 -0.1563 0.9271 0.0019
-11.500 -0.5270 0.02121 0.01747 -0.1602 0.9095 0.0019
-11.250 -0.5069 0.01980 0.01585 -0.1615 0.8935 0.0020
-11.000 -0.4872 0.01865 0.01451 -0.1619 0.8801 0.0020
-10.750 -0.4667 0.01764 0.01332 -0.1622 0.8682 0.0020
-10.500 -0.4449 0.01678 0.01229 -0.1623 0.8574 0.0020
-10.250 -0.4219 0.01600 0.01138 -0.1624 0.8481 0.0021
-10.000 -0.3982 0.01533 0.01057 -0.1625 0.8397 0.0021
-9.750 -0.3738 0.01470 0.00981 -0.1626 0.8312 0.0021
-9.500 -0.3497 0.01385 0.00879 -0.1628 0.8235 0.0023
-9.250 -0.3242 0.01326 0.00808 -0.1630 0.8161 0.0024
-9.000 -0.2984 0.01275 0.00746 -0.1631 0.8094 0.0026
-8.750 -0.2718 0.01230 0.00693 -0.1633 0.8027 0.0028
-8.250 -0.2181 0.01155 0.00600 -0.1636 0.7906 0.0032
-8.000 -0.1908 0.01122 0.00559 -0.1637 0.7845 0.0035
-7.750 -0.1636 0.01089 0.00518 -0.1639 0.7790 0.0039
-7.500 -0.1359 0.01056 0.00480 -0.1641 0.7734 0.0047
-7.250 -0.1083 0.01028 0.00445 -0.1643 0.7678 0.0058
-7.000 -0.0804 0.01000 0.00413 -0.1645 0.7628 0.0076
-6.750 -0.0523 0.00971 0.00382 -0.1647 0.7576 0.0105
-6.500 -0.0244 0.00947 0.00354 -0.1649 0.7525 0.0139
-6.250 0.0037 0.00923 0.00328 -0.1652 0.7478 0.0183
-6.000 0.0321 0.00902 0.00306 -0.1654 0.7428 0.0232
-5.750 0.0603 0.00881 0.00285 -0.1657 0.7379 0.0298
-5.500 0.0886 0.00861 0.00265 -0.1659 0.7335 0.0387
-5.250 0.1172 0.00839 0.00246 -0.1662 0.7289 0.0501
-5.000 0.1456 0.00821 0.00230 -0.1665 0.7242 0.0611
-4.750 0.1739 0.00808 0.00216 -0.1667 0.7197 0.0708
-4.500 0.2027 0.00793 0.00203 -0.1670 0.7155 0.0818
-4.250 0.2314 0.00781 0.00192 -0.1672 0.7110 0.0925
-4.000 0.2598 0.00771 0.00181 -0.1674 0.7065 0.1035
-3.750 0.2884 0.00762 0.00172 -0.1676 0.7025 0.1143
-3.500 0.3172 0.00752 0.00164 -0.1679 0.6982 0.1263
-3.250 0.3458 0.00743 0.00157 -0.1681 0.6936 0.1411
-3.000 0.3741 0.00738 0.00150 -0.1682 0.6894 0.1544
-2.750 0.4030 0.00729 0.00145 -0.1685 0.6853 0.1690
-2.500 0.4316 0.00723 0.00141 -0.1687 0.6808 0.1831
-2.250 0.4600 0.00718 0.00137 -0.1689 0.6763 0.1986
-2.000 0.4886 0.00713 0.00135 -0.1691 0.6721 0.2134
-1.750 0.5173 0.00709 0.00133 -0.1693 0.6675 0.2288
-1.500 0.5456 0.00706 0.00131 -0.1694 0.6627 0.2429
-1.250 0.5739 0.00704 0.00131 -0.1696 0.6583 0.2588
-1.000 0.6026 0.00701 0.00131 -0.1698 0.6535 0.2738
-0.750 0.6309 0.00700 0.00132 -0.1699 0.6485 0.2898
-0.500 0.6589 0.00700 0.00133 -0.1700 0.6438 0.3046
-0.250 0.6875 0.00698 0.00135 -0.1702 0.6389 0.3216
0.000 0.7156 0.00698 0.00138 -0.1703 0.6334 0.3389
0.250 0.7435 0.00700 0.00141 -0.1703 0.6283 0.3556
0.500 0.7719 0.00699 0.00145 -0.1705 0.6225 0.3737
0.750 0.7996 0.00701 0.00150 -0.1705 0.6162 0.3924
1.000 0.8276 0.00702 0.00155 -0.1706 0.6101 0.4125
1.250 0.8552 0.00705 0.00161 -0.1706 0.6029 0.4328
1.500 0.8828 0.00708 0.00168 -0.1706 0.5959 0.4544
1.750 0.9103 0.00712 0.00176 -0.1706 0.5877 0.4769
2.000 0.9376 0.00717 0.00184 -0.1706 0.5795 0.5003
2.250 0.9643 0.00724 0.00193 -0.1704 0.5697 0.5252
2.500 0.9914 0.00730 0.00204 -0.1703 0.5595 0.5507
2.750 1.0181 0.00738 0.00215 -0.1702 0.5493 0.5772
3.000 1.0443 0.00748 0.00227 -0.1699 0.5378 0.6044
3.250 1.0703 0.00759 0.00242 -0.1697 0.5250 0.6325
3.500 1.0963 0.00770 0.00256 -0.1694 0.5118 0.6618
3.750 1.1219 0.00782 0.00272 -0.1690 0.4985 0.6928
4.000 1.1471 0.00796 0.00290 -0.1686 0.4840 0.7264
4.250 1.1715 0.00813 0.00310 -0.1680 0.4677 0.7619
4.750 1.2167 0.00852 0.00355 -0.1661 0.4286 0.8498
5.000 1.2329 0.00868 0.00377 -0.1636 0.4070 0.9223
5.250 1.2531 0.00896 0.00399 -0.1622 0.3829 1.0000
5.500 1.2739 0.00940 0.00430 -0.1610 0.3557 1.0000
5.750 1.2931 0.00990 0.00465 -0.1596 0.3238 1.0000
6.000 1.3120 0.01041 0.00501 -0.1581 0.2954 1.0000
6.250 1.3299 0.01095 0.00541 -0.1564 0.2664 1.0000
6.500 1.3464 0.01152 0.00583 -0.1545 0.2372 1.0000
6.750 1.3603 0.01211 0.00628 -0.1520 0.2095 1.0000
7.000 1.3717 0.01278 0.00679 -0.1492 0.1789 1.0000
7.250 1.3845 0.01340 0.00728 -0.1466 0.1552 1.0000
7.500 1.3990 0.01395 0.00776 -0.1444 0.1385 1.0000
7.750 1.4125 0.01456 0.00828 -0.1420 0.1202 1.0000
8.000 1.4236 0.01529 0.00891 -0.1394 0.1009 1.0000
8.250 1.4350 0.01603 0.00956 -0.1368 0.0830 1.0000
8.500 1.4461 0.01680 0.01026 -0.1343 0.0681 1.0000
8.750 1.4580 0.01755 0.01096 -0.1320 0.0569 1.0000
9.000 1.4690 0.01837 0.01173 -0.1296 0.0464 1.0000
9.250 1.4803 0.01921 0.01254 -0.1274 0.0381 1.0000
9.500 1.4913 0.02010 0.01341 -0.1252 0.0309 1.0000
9.750 1.5024 0.02101 0.01431 -0.1231 0.0254 1.0000
10.000 1.5131 0.02199 0.01528 -0.1211 0.0209 1.0000
10.250 1.5233 0.02302 0.01632 -0.1191 0.0168 1.0000
10.500 1.5341 0.02407 0.01737 -0.1172 0.0138 1.0000
10.750 1.5449 0.02514 0.01847 -0.1155 0.0115 1.0000
11.000 1.5546 0.02632 0.01967 -0.1137 0.0093 1.0000
11.250 1.5644 0.02755 0.02092 -0.1120 0.0076 1.0000
11.500 1.5746 0.02877 0.02219 -0.1104 0.0064 1.0000
11.750 1.5837 0.03012 0.02357 -0.1088 0.0053 1.0000
12.000 1.5931 0.03147 0.02496 -0.1074 0.0045 1.0000
12.250 1.6015 0.03296 0.02650 -0.1059 0.0039 1.0000
12.500 1.6105 0.03443 0.02803 -0.1046 0.0035 1.0000
12.750 1.6189 0.03599 0.02965 -0.1033 0.0031 1.0000
13.000 1.6264 0.03767 0.03138 -0.1020 0.0028 1.0000
13.250 1.6337 0.03943 0.03320 -0.1009 0.0025 1.0000
13.500 1.6411 0.04122 0.03505 -0.0998 0.0023 1.0000
13.750 1.6480 0.04309 0.03700 -0.0988 0.0022 1.0000
14.000 1.6542 0.04509 0.03906 -0.0978 0.0020 1.0000
14.250 1.6598 0.04722 0.04126 -0.0969 0.0018 1.0000
14.500 1.6644 0.04951 0.04363 -0.0961 0.0017 1.0000
14.750 1.6682 0.05194 0.04613 -0.0954 0.0015 1.0000
15.000 1.6731 0.05430 0.04857 -0.0948 0.0015 1.0000
15.250 1.6771 0.05682 0.05117 -0.0942 0.0014 1.0000
15.500 1.6805 0.05948 0.05392 -0.0938 0.0013 1.0000
15.750 1.6833 0.06230 0.05682 -0.0935 0.0012 1.0000
16.000 1.6856 0.06522 0.05983 -0.0933 0.0012 1.0000
16.250 1.6870 0.06832 0.06302 -0.0932 0.0011 1.0000
16.500 1.6877 0.07160 0.06638 -0.0933 0.0011 1.0000
16.750 1.6877 0.07506 0.06994 -0.0934 0.0010 1.0000
17.000 1.6867 0.07873 0.07371 -0.0938 0.0010 1.0000
17.250 1.6852 0.08255 0.07763 -0.0943 0.0009 1.0000
17.500 1.6826 0.08661 0.08179 -0.0949 0.0009 1.0000
17.750 1.6790 0.09092 0.08621 -0.0958 0.0008 1.0000
18.000 1.6748 0.09541 0.09081 -0.0968 0.0008 1.0000
18.250 1.6690 0.10025 0.09577 -0.0981 0.0008 1.0000
18.500 1.6621 0.10536 0.10099 -0.0996 0.0008 1.0000
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