E387 (e387-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E387 (e387-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.51 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e387-il-1000000-n5.txt Download as CSV file: xf-e387-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2638 0.09155 0.08951 -0.0308 0.8191 0.0065
-9.250 -0.3617 0.09497 0.09335 -0.0271 0.9841 0.0048
-9.000 -0.3276 0.08831 0.08661 -0.0387 0.9443 0.0046
-8.750 -0.3114 0.08330 0.08134 -0.0448 0.8731 0.0045
-8.500 -0.3089 0.08099 0.07885 -0.0451 0.8287 0.0044
-8.250 -0.3120 0.07698 0.07475 -0.0464 0.8012 0.0044
-8.000 -0.3122 0.07381 0.07151 -0.0476 0.7804 0.0043
-7.750 -0.3184 0.07001 0.06768 -0.0488 0.7627 0.0043
-7.500 -0.3197 0.06605 0.06368 -0.0520 0.7482 0.0043
-7.250 -0.3204 0.05922 0.05680 -0.0590 0.7357 0.0044
-7.000 -0.3129 0.05281 0.05030 -0.0656 0.7248 0.0043
-6.750 -0.3321 0.02422 0.02067 -0.0793 0.7204 0.0047
-6.500 -0.3129 0.02010 0.01598 -0.0797 0.7111 0.0048
-6.250 -0.2894 0.01807 0.01359 -0.0798 0.7023 0.0048
-6.000 -0.2645 0.01670 0.01192 -0.0797 0.6937 0.0049
-5.750 -0.2388 0.01553 0.01050 -0.0796 0.6855 0.0049
-5.500 -0.2133 0.01421 0.00889 -0.0795 0.6780 0.0051
-5.250 -0.1878 0.01283 0.00726 -0.0794 0.6705 0.0053
-5.000 -0.1611 0.01219 0.00649 -0.0794 0.6637 0.0055
-4.750 -0.1340 0.01156 0.00573 -0.0793 0.6572 0.0056
-4.250 -0.0796 0.01048 0.00442 -0.0791 0.6447 0.0058
-4.000 -0.0522 0.01005 0.00389 -0.0790 0.6384 0.0060
-3.750 -0.0246 0.00967 0.00343 -0.0789 0.6330 0.0062
-3.500 0.0032 0.00934 0.00303 -0.0789 0.6270 0.0066
-3.000 0.0590 0.00884 0.00240 -0.0788 0.6163 0.0073
-2.750 0.0870 0.00866 0.00217 -0.0788 0.6107 0.0076
-2.500 0.1149 0.00842 0.00185 -0.0788 0.6056 0.0081
-2.250 0.1430 0.00823 0.00162 -0.0788 0.6008 0.0089
-2.000 0.1711 0.00810 0.00145 -0.0788 0.5954 0.0100
-1.750 0.1992 0.00800 0.00130 -0.0788 0.5906 0.0109
-1.500 0.2275 0.00788 0.00117 -0.0789 0.5856 0.0144
-1.250 0.2554 0.00767 0.00106 -0.0789 0.5805 0.0454
-1.000 0.2834 0.00753 0.00099 -0.0790 0.5758 0.0770
-0.750 0.3113 0.00731 0.00094 -0.0791 0.5709 0.1348
-0.500 0.3393 0.00716 0.00091 -0.0792 0.5660 0.1845
-0.250 0.3671 0.00698 0.00089 -0.0793 0.5614 0.2512
0.000 0.3949 0.00674 0.00089 -0.0794 0.5564 0.3406
0.250 0.4224 0.00649 0.00091 -0.0795 0.5515 0.4443
0.500 0.4500 0.00633 0.00093 -0.0796 0.5469 0.5224
0.750 0.4776 0.00616 0.00096 -0.0796 0.5417 0.6008
1.000 0.5042 0.00593 0.00101 -0.0794 0.5365 0.7111
1.250 0.5288 0.00565 0.00107 -0.0786 0.5315 0.8335
1.500 0.5554 0.00541 0.00110 -0.0780 0.5249 0.9643
1.750 0.5895 0.00547 0.00112 -0.0794 0.5176 1.0000
2.000 0.6173 0.00555 0.00116 -0.0794 0.5093 1.0000
2.250 0.6450 0.00563 0.00120 -0.0794 0.5008 1.0000
2.750 0.7003 0.00582 0.00132 -0.0793 0.4820 1.0000
3.000 0.7279 0.00593 0.00139 -0.0793 0.4725 1.0000
3.250 0.7553 0.00606 0.00147 -0.0792 0.4615 1.0000
3.500 0.7827 0.00619 0.00157 -0.0792 0.4492 1.0000
3.750 0.8097 0.00635 0.00168 -0.0791 0.4331 1.0000
4.000 0.8359 0.00661 0.00181 -0.0789 0.4020 1.0000
4.250 0.8614 0.00696 0.00200 -0.0787 0.3651 1.0000
4.500 0.8867 0.00735 0.00223 -0.0784 0.3263 1.0000
4.750 0.9077 0.00826 0.00269 -0.0776 0.2387 1.0000
5.000 0.9298 0.00903 0.00313 -0.0769 0.1723 1.0000
5.250 0.9531 0.00963 0.00351 -0.0764 0.1295 1.0000
5.500 0.9763 0.01022 0.00391 -0.0759 0.0907 1.0000
5.750 0.9996 0.01079 0.00431 -0.0754 0.0587 1.0000
6.000 1.0221 0.01142 0.00478 -0.0747 0.0290 1.0000
6.250 1.0447 0.01203 0.00528 -0.0741 0.0098 1.0000
6.500 1.0695 0.01237 0.00564 -0.0737 0.0085 1.0000
6.750 1.0940 0.01272 0.00600 -0.0733 0.0076 1.0000
7.000 1.1181 0.01311 0.00643 -0.0728 0.0070 1.0000
7.250 1.1422 0.01346 0.00682 -0.0723 0.0068 1.0000
7.500 1.1659 0.01386 0.00726 -0.0718 0.0065 1.0000
7.750 1.1892 0.01427 0.00771 -0.0712 0.0061 1.0000
8.000 1.2118 0.01473 0.00821 -0.0706 0.0059 1.0000
8.250 1.2338 0.01522 0.00875 -0.0698 0.0056 1.0000
8.500 1.2553 0.01574 0.00931 -0.0690 0.0054 1.0000
8.750 1.2760 0.01631 0.00994 -0.0681 0.0053 1.0000
9.000 1.2956 0.01694 0.01062 -0.0671 0.0051 1.0000
9.250 1.3138 0.01764 0.01138 -0.0658 0.0049 1.0000
9.500 1.3299 0.01847 0.01228 -0.0643 0.0048 1.0000
9.750 1.3430 0.01945 0.01335 -0.0624 0.0046 1.0000
10.000 1.3531 0.02048 0.01448 -0.0600 0.0045 1.0000
10.250 1.3643 0.02121 0.01528 -0.0577 0.0045 1.0000
10.500 1.3736 0.02205 0.01618 -0.0553 0.0044 1.0000
10.750 1.3824 0.02296 0.01718 -0.0530 0.0044 1.0000
11.000 1.3902 0.02402 0.01831 -0.0508 0.0043 1.0000
11.250 1.3969 0.02524 0.01962 -0.0488 0.0043 1.0000
11.500 1.4048 0.02646 0.02092 -0.0471 0.0042 1.0000
11.750 1.4087 0.02810 0.02266 -0.0454 0.0041 1.0000
12.000 1.4141 0.02972 0.02437 -0.0440 0.0041 1.0000
12.250 1.4212 0.03128 0.02602 -0.0429 0.0039 1.0000
12.500 1.4248 0.03324 0.02809 -0.0418 0.0039 1.0000
12.750 1.4309 0.03506 0.02999 -0.0410 0.0037 1.0000
13.000 1.4331 0.03732 0.03236 -0.0402 0.0037 1.0000
13.250 1.4370 0.03950 0.03464 -0.0397 0.0036 1.0000
13.500 1.4377 0.04210 0.03735 -0.0392 0.0036 1.0000
13.750 1.4390 0.04472 0.04007 -0.0389 0.0035 1.0000
14.000 1.4394 0.04752 0.04297 -0.0388 0.0035 1.0000
14.250 1.4382 0.05057 0.04614 -0.0388 0.0034 1.0000
14.500 1.4353 0.05393 0.04962 -0.0390 0.0034 1.0000
14.750 1.4341 0.05721 0.05301 -0.0394 0.0034 1.0000
15.000 1.4307 0.06087 0.05680 -0.0400 0.0034 1.0000
15.250 1.4271 0.06474 0.06079 -0.0409 0.0033 1.0000
15.500 1.4226 0.06891 0.06507 -0.0420 0.0033 1.0000
15.750 1.4179 0.07323 0.06951 -0.0433 0.0033 1.0000
16.000 1.4116 0.07796 0.07437 -0.0449 0.0032 1.0000
16.250 1.4031 0.08325 0.07980 -0.0469 0.0032 1.0000
16.500 1.3956 0.08854 0.08521 -0.0491 0.0032 1.0000
16.750 1.3862 0.09435 0.09116 -0.0516 0.0032 1.0000
17.000 1.3770 0.10036 0.09729 -0.0544 0.0032 1.0000
17.250 1.3654 0.10698 0.10405 -0.0577 0.0031 1.0000
17.500 1.3537 0.11381 0.11101 -0.0612 0.0031 1.0000
17.750 1.3432 0.12064 0.11796 -0.0649 0.0031 1.0000
18.000 1.3296 0.12832 0.12578 -0.0691 0.0031 1.0000
18.250 1.3170 0.13598 0.13357 -0.0735 0.0031 1.0000
18.500 1.3023 0.14436 0.14208 -0.0785 0.0031 1.0000
18.750 1.2887 0.15274 0.15059 -0.0836 0.0031 1.0000
19.000 1.2736 0.16176 0.15975 -0.0892 0.0031 1.0000
19.250 1.2588 0.17102 0.16914 -0.0950 0.0031 1.0000
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Polar data table (+)
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