E387 (e387-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E387 (e387-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.58 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e387-il-1000000.txt Download as CSV file: xf-e387-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E387
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2739 0.08430 0.08284 -0.0309 1.0000 0.0092
-9.000 -0.2707 0.08091 0.07947 -0.0318 1.0000 0.0094
-8.750 -0.2687 0.07723 0.07580 -0.0328 1.0000 0.0094
-8.500 -0.2612 0.07279 0.07136 -0.0357 0.9815 0.0095
-8.250 -0.2450 0.06713 0.06566 -0.0416 0.9507 0.0098
-8.000 -0.2395 0.06295 0.06134 -0.0442 0.9003 0.0099
-7.750 -0.2413 0.05953 0.05779 -0.0448 0.8629 0.0100
-7.500 -0.2439 0.05599 0.05415 -0.0457 0.8366 0.0101
-7.250 -0.2478 0.05244 0.05053 -0.0468 0.8143 0.0104
-7.000 -0.2537 0.04888 0.04692 -0.0484 0.7960 0.0103
-6.750 -0.2536 0.04410 0.04208 -0.0530 0.7813 0.0105
-6.500 -0.2493 0.03842 0.03632 -0.0588 0.7690 0.0107
-6.250 -0.2494 0.04533 0.04302 -0.0747 0.7945 0.0105
-6.000 -0.2329 0.03899 0.03643 -0.0783 0.7798 0.0111
-5.750 -0.2112 0.03159 0.02859 -0.0802 0.7676 0.0121
-5.500 -0.1998 0.02305 0.01929 -0.0819 0.7564 0.0127
-5.250 -0.1764 0.02149 0.01758 -0.0821 0.7450 0.0132
-5.000 -0.1518 0.02024 0.01615 -0.0822 0.7346 0.0139
-4.500 -0.1011 0.01385 0.00869 -0.0811 0.7163 0.0115
-4.250 -0.0747 0.01247 0.00704 -0.0808 0.7079 0.0112
-4.000 -0.0476 0.01153 0.00593 -0.0806 0.6994 0.0112
-3.750 -0.0203 0.01092 0.00519 -0.0804 0.6917 0.0115
-3.500 0.0068 0.01013 0.00426 -0.0802 0.6840 0.0114
-3.250 0.0342 0.00950 0.00353 -0.0800 0.6772 0.0113
-3.000 0.0617 0.00903 0.00296 -0.0798 0.6701 0.0115
-2.750 0.0896 0.00869 0.00253 -0.0797 0.6637 0.0119
-2.500 0.1175 0.00829 0.00204 -0.0797 0.6572 0.0129
-2.250 0.1453 0.00806 0.00173 -0.0796 0.6513 0.0145
-2.000 0.1736 0.00790 0.00152 -0.0796 0.6451 0.0161
-1.750 0.2015 0.00764 0.00132 -0.0796 0.6393 0.0387
-1.500 0.2292 0.00732 0.00120 -0.0796 0.6339 0.1031
-1.000 0.2846 0.00686 0.00109 -0.0798 0.6227 0.2388
-0.750 0.3123 0.00655 0.00106 -0.0800 0.6174 0.3406
-0.500 0.3393 0.00617 0.00107 -0.0800 0.6120 0.4832
-0.250 0.3659 0.00583 0.00109 -0.0799 0.6069 0.6230
0.000 0.3915 0.00547 0.00113 -0.0794 0.6017 0.7634
0.250 0.4124 0.00505 0.00116 -0.0774 0.5967 0.9460
0.500 0.4530 0.00505 0.00113 -0.0802 0.5914 1.0000
0.750 0.4808 0.00510 0.00113 -0.0802 0.5861 1.0000
1.000 0.5085 0.00518 0.00114 -0.0801 0.5808 1.0000
1.250 0.5365 0.00522 0.00116 -0.0801 0.5754 1.0000
1.500 0.5643 0.00528 0.00118 -0.0801 0.5693 1.0000
1.750 0.5921 0.00536 0.00122 -0.0800 0.5633 1.0000
2.000 0.6200 0.00541 0.00125 -0.0800 0.5565 1.0000
2.250 0.6476 0.00550 0.00129 -0.0800 0.5497 1.0000
2.500 0.6756 0.00556 0.00134 -0.0800 0.5423 1.0000
2.750 0.7032 0.00565 0.00140 -0.0800 0.5353 1.0000
3.000 0.7310 0.00571 0.00146 -0.0800 0.5277 1.0000
3.250 0.7586 0.00581 0.00152 -0.0799 0.5202 1.0000
3.500 0.7863 0.00589 0.00159 -0.0799 0.5115 1.0000
3.750 0.8139 0.00598 0.00169 -0.0799 0.5028 1.0000
4.000 0.8412 0.00610 0.00178 -0.0798 0.4931 1.0000
4.250 0.8686 0.00621 0.00187 -0.0798 0.4815 1.0000
4.500 0.8955 0.00637 0.00198 -0.0797 0.4649 1.0000
4.750 0.9218 0.00659 0.00212 -0.0795 0.4383 1.0000
5.000 0.9477 0.00686 0.00228 -0.0792 0.4078 1.0000
5.250 0.9729 0.00721 0.00249 -0.0789 0.3712 1.0000
5.500 0.9963 0.00778 0.00280 -0.0784 0.3159 1.0000
5.750 1.0177 0.00858 0.00327 -0.0776 0.2473 1.0000
6.000 1.0387 0.00942 0.00377 -0.0768 0.1837 1.0000
6.250 1.0598 0.01021 0.00428 -0.0760 0.1300 1.0000
6.500 1.0799 0.01108 0.00486 -0.0751 0.0775 1.0000
6.750 1.0978 0.01219 0.00563 -0.0738 0.0237 1.0000
7.000 1.1198 0.01281 0.00619 -0.0730 0.0127 1.0000
7.250 1.1427 0.01330 0.00671 -0.0723 0.0107 1.0000
7.500 1.1655 0.01380 0.00727 -0.0716 0.0099 1.0000
7.750 1.1880 0.01428 0.00782 -0.0709 0.0095 1.0000
8.000 1.2098 0.01482 0.00842 -0.0700 0.0091 1.0000
8.250 1.2309 0.01540 0.00906 -0.0691 0.0088 1.0000
8.500 1.2510 0.01604 0.00975 -0.0681 0.0085 1.0000
8.750 1.2700 0.01672 0.01050 -0.0669 0.0083 1.0000
9.000 1.2877 0.01748 0.01133 -0.0655 0.0079 1.0000
9.250 1.3032 0.01836 0.01229 -0.0638 0.0077 1.0000
9.500 1.3131 0.01958 0.01359 -0.0614 0.0074 1.0000
9.750 1.3162 0.02099 0.01512 -0.0579 0.0072 1.0000
10.000 1.3212 0.02210 0.01631 -0.0548 0.0072 1.0000
10.250 1.3169 0.02405 0.01837 -0.0508 0.0070 1.0000
10.500 1.3263 0.02510 0.01951 -0.0489 0.0070 1.0000
10.750 1.3369 0.02612 0.02060 -0.0472 0.0068 1.0000
11.000 1.3464 0.02728 0.02185 -0.0456 0.0067 1.0000
11.250 1.3529 0.02882 0.02349 -0.0439 0.0066 1.0000
11.500 1.3587 0.03056 0.02532 -0.0423 0.0065 1.0000
11.750 1.3648 0.03232 0.02719 -0.0409 0.0065 1.0000
12.000 1.3710 0.03413 0.02910 -0.0397 0.0064 1.0000
12.250 1.3750 0.03641 0.03151 -0.0384 0.0064 1.0000
12.500 1.3797 0.03854 0.03375 -0.0373 0.0063 1.0000
12.750 1.3835 0.04084 0.03618 -0.0364 0.0062 1.0000
13.000 1.3856 0.04342 0.03891 -0.0356 0.0062 1.0000
13.250 1.3867 0.04610 0.04173 -0.0350 0.0061 1.0000
13.500 1.3866 0.04898 0.04474 -0.0346 0.0060 1.0000
13.750 1.3824 0.05260 0.04855 -0.0343 0.0061 1.0000
14.000 1.3796 0.05590 0.05200 -0.0344 0.0060 1.0000
14.250 1.3697 0.06052 0.05683 -0.0347 0.0061 1.0000
14.500 1.3641 0.06439 0.06083 -0.0355 0.0060 1.0000
14.750 1.3539 0.06920 0.06582 -0.0366 0.0059 1.0000
15.000 1.3433 0.07431 0.07109 -0.0382 0.0059 1.0000
15.250 1.3305 0.08005 0.07701 -0.0403 0.0059 1.0000
15.500 1.3141 0.08672 0.08387 -0.0430 0.0059 1.0000
15.750 1.2981 0.09370 0.09102 -0.0463 0.0059 1.0000
16.000 1.2835 0.10077 0.09824 -0.0499 0.0059 1.0000
16.250 1.2641 0.10921 0.10686 -0.0545 0.0059 1.0000
16.500 1.2430 0.11858 0.11641 -0.0599 0.0060 1.0000
16.750 1.2216 0.12859 0.12658 -0.0660 0.0061 1.0000
17.000 1.2000 0.13925 0.13740 -0.0727 0.0062 1.0000
17.250 1.1783 0.15072 0.14900 -0.0800 0.0063 1.0000
17.500 1.1542 0.16377 0.16218 -0.0883 0.0065 1.0000
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Polar data table (+)
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