EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 396 AIRFOIL (e396-il) Reynolds number: 500,000 Max Cl/Cd: 135.14 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e396-il-500000.txt Download as CSV file: xf-e396-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 396 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 -0.4096 0.07055 0.06805 -0.0911 0.9861 0.0084
-11.500 -0.4279 0.05951 0.05683 -0.1025 0.9796 0.0083
-11.250 -0.4287 0.05165 0.04883 -0.1123 0.9722 0.0082
-11.000 -0.4265 0.04498 0.04199 -0.1210 0.9614 0.0081
-10.750 -0.4264 0.03466 0.03133 -0.1379 0.9479 0.0082
-10.500 -0.4057 0.02721 0.02339 -0.1541 0.9338 0.0084
-10.250 -0.3846 0.02430 0.02019 -0.1586 0.9220 0.0086
-10.000 -0.3626 0.02248 0.01817 -0.1608 0.9115 0.0089
-9.750 -0.3391 0.02114 0.01664 -0.1622 0.9020 0.0093
-9.500 -0.3192 0.01992 0.01523 -0.1624 0.8916 0.0096
-9.250 -0.2970 0.01883 0.01395 -0.1628 0.8830 0.0100
-9.000 -0.2741 0.01780 0.01273 -0.1630 0.8750 0.0104
-8.750 -0.2505 0.01696 0.01172 -0.1631 0.8673 0.0110
-8.500 -0.2274 0.01577 0.01033 -0.1634 0.8602 0.0120
-8.250 -0.2025 0.01510 0.00959 -0.1636 0.8535 0.0133
-8.000 -0.1762 0.01461 0.00899 -0.1637 0.8473 0.0149
-7.750 -0.1507 0.01369 0.00794 -0.1640 0.8414 0.0177
-7.500 -0.1241 0.01329 0.00745 -0.1640 0.8352 0.0210
-7.250 -0.0968 0.01264 0.00672 -0.1644 0.8302 0.0272
-7.000 -0.0701 0.01218 0.00623 -0.1646 0.8246 0.0339
-6.750 -0.0427 0.01181 0.00580 -0.1648 0.8192 0.0405
-6.500 -0.0142 0.01160 0.00551 -0.1651 0.8147 0.0466
-6.250 0.0129 0.01123 0.00515 -0.1652 0.8094 0.0551
-6.000 0.0409 0.01095 0.00483 -0.1655 0.8045 0.0641
-5.750 0.0696 0.01076 0.00455 -0.1658 0.8002 0.0736
-5.500 0.0972 0.01051 0.00431 -0.1659 0.7953 0.0847
-5.250 0.1254 0.01027 0.00406 -0.1661 0.7906 0.0979
-5.000 0.1543 0.01009 0.00385 -0.1665 0.7865 0.1120
-4.750 0.1823 0.00990 0.00367 -0.1667 0.7820 0.1266
-4.500 0.2106 0.00973 0.00350 -0.1669 0.7774 0.1422
-4.250 0.2393 0.00957 0.00335 -0.1672 0.7734 0.1597
-4.000 0.2679 0.00945 0.00324 -0.1674 0.7693 0.1769
-3.750 0.2961 0.00933 0.00314 -0.1676 0.7647 0.1958
-3.500 0.3247 0.00924 0.00304 -0.1678 0.7606 0.2148
-3.250 0.3539 0.00917 0.00297 -0.1682 0.7569 0.2341
-3.000 0.3819 0.00907 0.00292 -0.1683 0.7525 0.2525
-2.750 0.4103 0.00900 0.00286 -0.1685 0.7482 0.2723
-2.500 0.4392 0.00895 0.00280 -0.1687 0.7444 0.2913
-2.250 0.4678 0.00890 0.00278 -0.1690 0.7405 0.3113
-2.000 0.4959 0.00885 0.00276 -0.1691 0.7360 0.3308
-1.750 0.5245 0.00880 0.00273 -0.1693 0.7319 0.3515
-1.500 0.5537 0.00879 0.00272 -0.1696 0.7282 0.3730
-1.250 0.5815 0.00874 0.00274 -0.1697 0.7238 0.3952
-1.000 0.6098 0.00870 0.00274 -0.1698 0.7194 0.4181
-0.750 0.6385 0.00868 0.00275 -0.1700 0.7155 0.4426
-0.250 0.6947 0.00863 0.00283 -0.1703 0.7067 0.4959
0.000 0.7230 0.00861 0.00286 -0.1704 0.7025 0.5244
0.250 0.7518 0.00863 0.00291 -0.1707 0.6986 0.5545
0.500 0.7791 0.00859 0.00298 -0.1706 0.6938 0.5854
0.750 0.8070 0.00857 0.00304 -0.1706 0.6892 0.6181
1.000 0.8354 0.00859 0.00310 -0.1708 0.6851 0.6519
1.250 0.8622 0.00856 0.00321 -0.1706 0.6802 0.6872
1.500 0.8892 0.00854 0.00328 -0.1704 0.6753 0.7244
1.750 0.9163 0.00855 0.00336 -0.1702 0.6709 0.7633
2.000 0.9413 0.00852 0.00347 -0.1695 0.6656 0.8048
2.250 0.9647 0.00847 0.00354 -0.1685 0.6603 0.8518
2.500 0.9845 0.00841 0.00356 -0.1665 0.6556 0.9141
2.750 1.0105 0.00834 0.00358 -0.1660 0.6496 1.0000
3.000 1.0384 0.00843 0.00363 -0.1661 0.6439 1.0000
3.250 1.0659 0.00853 0.00372 -0.1662 0.6378 1.0000
3.500 1.0927 0.00861 0.00380 -0.1660 0.6309 1.0000
3.750 1.1197 0.00872 0.00389 -0.1660 0.6242 1.0000
4.000 1.1461 0.00881 0.00399 -0.1657 0.6169 1.0000
4.250 1.1726 0.00893 0.00410 -0.1655 0.6098 1.0000
4.500 1.1983 0.00904 0.00421 -0.1652 0.6015 1.0000
4.750 1.2239 0.00916 0.00434 -0.1648 0.5932 1.0000
5.000 1.2493 0.00931 0.00447 -0.1644 0.5850 1.0000
5.250 1.2743 0.00944 0.00464 -0.1640 0.5758 1.0000
5.500 1.2987 0.00961 0.00480 -0.1634 0.5662 1.0000
5.750 1.3223 0.00980 0.00497 -0.1626 0.5553 1.0000
6.000 1.3458 0.00998 0.00516 -0.1619 0.5439 1.0000
6.250 1.3687 0.01018 0.00539 -0.1610 0.5321 1.0000
6.500 1.3908 0.01042 0.00562 -0.1600 0.5196 1.0000
6.750 1.4115 0.01068 0.00587 -0.1587 0.5048 1.0000
7.000 1.4309 0.01099 0.00614 -0.1572 0.4884 1.0000
7.250 1.4490 0.01134 0.00646 -0.1555 0.4712 1.0000
7.500 1.4645 0.01174 0.00682 -0.1533 0.4516 1.0000
7.750 1.4776 0.01217 0.00720 -0.1506 0.4306 1.0000
8.000 1.4875 0.01273 0.00766 -0.1475 0.4070 1.0000
8.250 1.4952 0.01340 0.00823 -0.1440 0.3802 1.0000
8.500 1.5015 0.01419 0.00890 -0.1404 0.3512 1.0000
8.750 1.5065 0.01510 0.00967 -0.1369 0.3219 1.0000
9.000 1.5104 0.01613 0.01057 -0.1333 0.2929 1.0000
9.250 1.5131 0.01729 0.01159 -0.1297 0.2638 1.0000
9.500 1.5151 0.01858 0.01276 -0.1262 0.2358 1.0000
9.750 1.5168 0.01999 0.01403 -0.1230 0.2094 1.0000
10.000 1.5200 0.02139 0.01533 -0.1201 0.1852 1.0000
10.250 1.5232 0.02289 0.01673 -0.1174 0.1636 1.0000
10.500 1.5256 0.02451 0.01825 -0.1148 0.1428 1.0000
10.750 1.5289 0.02615 0.01982 -0.1124 0.1244 1.0000
11.000 1.5318 0.02789 0.02149 -0.1102 0.1066 1.0000
11.250 1.5343 0.02974 0.02327 -0.1080 0.0911 1.0000
11.500 1.5365 0.03168 0.02514 -0.1060 0.0770 1.0000
11.750 1.5391 0.03367 0.02709 -0.1042 0.0645 1.0000
12.000 1.5415 0.03574 0.02914 -0.1025 0.0534 1.0000
12.250 1.5449 0.03779 0.03118 -0.1009 0.0449 1.0000
12.500 1.5481 0.03993 0.03333 -0.0995 0.0375 1.0000
12.750 1.5506 0.04222 0.03562 -0.0982 0.0317 1.0000
13.000 1.5534 0.04453 0.03795 -0.0970 0.0271 1.0000
13.250 1.5561 0.04692 0.04039 -0.0959 0.0231 1.0000
13.500 1.5583 0.04945 0.04295 -0.0949 0.0200 1.0000
13.750 1.5591 0.05221 0.04577 -0.0940 0.0172 1.0000
14.000 1.5621 0.05478 0.04841 -0.0933 0.0151 1.0000
14.250 1.5577 0.05834 0.05202 -0.0925 0.0131 1.0000
14.500 1.5608 0.06107 0.05485 -0.0920 0.0118 1.0000
14.750 1.5626 0.06401 0.05788 -0.0916 0.0106 1.0000
15.000 1.5569 0.06803 0.06199 -0.0914 0.0094 1.0000
15.250 1.5548 0.07168 0.06576 -0.0913 0.0086 1.0000
15.500 1.5562 0.07491 0.06910 -0.0913 0.0079 1.0000
15.750 1.5567 0.07835 0.07262 -0.0915 0.0073 1.0000
16.000 1.5531 0.08243 0.07679 -0.0919 0.0067 1.0000
16.250 1.5401 0.08809 0.08257 -0.0926 0.0063 1.0000
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