E387 (e387-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E387 (e387-il) Reynolds number: 200,000 Max Cl/Cd: 82.36 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e387-il-200000-n5.txt Download as CSV file: xf-e387-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3339 0.08673 0.08341 -0.0327 1.0000 0.0249
-7.750 -0.3337 0.08358 0.08032 -0.0339 1.0000 0.0252
-7.500 -0.3358 0.08060 0.07742 -0.0347 1.0000 0.0254
-7.250 -0.3289 0.07449 0.07138 -0.0473 0.9823 0.0272
-6.750 -0.2415 0.04444 0.04128 -0.0608 0.8734 0.0215
-6.250 -0.2466 0.04490 0.04116 -0.0773 0.8891 0.0155
-6.000 -0.2287 0.04034 0.03633 -0.0801 0.8694 0.0151
-5.750 -0.2104 0.03548 0.03109 -0.0821 0.8517 0.0146
-5.500 -0.1908 0.03077 0.02589 -0.0832 0.8362 0.0142
-5.250 -0.1694 0.02661 0.02114 -0.0837 0.8223 0.0138
-5.000 -0.1462 0.02324 0.01714 -0.0836 0.8097 0.0136
-4.500 -0.0958 0.01888 0.01174 -0.0829 0.7864 0.0137
-4.250 -0.0697 0.01746 0.00996 -0.0825 0.7758 0.0140
-4.000 -0.0435 0.01633 0.00854 -0.0820 0.7661 0.0145
-3.750 -0.0169 0.01552 0.00751 -0.0816 0.7562 0.0154
-3.500 0.0093 0.01471 0.00658 -0.0814 0.7471 0.0170
-3.250 0.0358 0.01409 0.00584 -0.0811 0.7386 0.0181
-3.000 0.0628 0.01354 0.00515 -0.0808 0.7299 0.0192
-2.750 0.0899 0.01311 0.00455 -0.0805 0.7223 0.0207
-2.500 0.1172 0.01269 0.00404 -0.0804 0.7142 0.0239
-2.250 0.1444 0.01232 0.00363 -0.0802 0.7073 0.0362
-2.000 0.1715 0.01186 0.00334 -0.0801 0.6997 0.0862
-1.750 0.1982 0.01147 0.00316 -0.0801 0.6933 0.1574
-1.500 0.2246 0.01098 0.00306 -0.0802 0.6860 0.2733
-1.250 0.2506 0.01059 0.00297 -0.0800 0.6800 0.3883
-1.000 0.2758 0.01013 0.00294 -0.0796 0.6732 0.5284
-0.750 0.2978 0.00963 0.00294 -0.0781 0.6672 0.6970
-0.500 0.3216 0.00920 0.00290 -0.0763 0.6615 0.8832
-0.250 0.3651 0.00912 0.00274 -0.0794 0.6549 1.0000
0.000 0.3922 0.00922 0.00268 -0.0792 0.6496 1.0000
0.250 0.4196 0.00930 0.00267 -0.0792 0.6431 1.0000
0.500 0.4468 0.00941 0.00265 -0.0790 0.6375 1.0000
0.750 0.4741 0.00951 0.00267 -0.0789 0.6318 1.0000
1.000 0.5015 0.00961 0.00270 -0.0788 0.6258 1.0000
1.250 0.5287 0.00974 0.00272 -0.0786 0.6208 1.0000
1.500 0.5561 0.00984 0.00280 -0.0786 0.6146 1.0000
1.750 0.5834 0.00995 0.00287 -0.0785 0.6090 1.0000
2.000 0.6107 0.01008 0.00295 -0.0784 0.6036 1.0000
2.250 0.6380 0.01020 0.00306 -0.0783 0.5975 1.0000
2.500 0.6652 0.01034 0.00315 -0.0781 0.5923 1.0000
2.750 0.6925 0.01046 0.00331 -0.0780 0.5857 1.0000
3.000 0.7196 0.01059 0.00342 -0.0779 0.5794 1.0000
3.250 0.7466 0.01072 0.00357 -0.0778 0.5723 1.0000
3.500 0.7735 0.01085 0.00371 -0.0776 0.5648 1.0000
3.750 0.8003 0.01098 0.00388 -0.0774 0.5561 1.0000
4.000 0.8269 0.01112 0.00401 -0.0771 0.5476 1.0000
4.250 0.8535 0.01125 0.00418 -0.0769 0.5375 1.0000
4.500 0.8800 0.01139 0.00439 -0.0767 0.5273 1.0000
4.750 0.9062 0.01154 0.00457 -0.0764 0.5165 1.0000
5.000 0.9322 0.01170 0.00475 -0.0760 0.5044 1.0000
5.250 0.9581 0.01186 0.00496 -0.0756 0.4907 1.0000
5.500 0.9836 0.01205 0.00522 -0.0753 0.4752 1.0000
5.750 1.0089 0.01225 0.00547 -0.0748 0.4569 1.0000
6.000 1.0319 0.01256 0.00569 -0.0740 0.4210 1.0000
6.250 1.0510 0.01320 0.00600 -0.0727 0.3514 1.0000
6.500 1.0673 0.01422 0.00663 -0.0712 0.2741 1.0000
6.750 1.0830 0.01538 0.00743 -0.0699 0.2081 1.0000
7.000 1.0992 0.01650 0.00826 -0.0686 0.1548 1.0000
7.250 1.1160 0.01754 0.00910 -0.0673 0.1131 1.0000
7.500 1.1310 0.01871 0.01003 -0.0659 0.0722 1.0000
7.750 1.1449 0.01992 0.01108 -0.0643 0.0399 1.0000
8.000 1.1588 0.02109 0.01215 -0.0626 0.0229 1.0000
8.250 1.1739 0.02210 0.01319 -0.0610 0.0181 1.0000
8.500 1.1894 0.02301 0.01420 -0.0594 0.0163 1.0000
8.750 1.2028 0.02403 0.01531 -0.0577 0.0152 1.0000
9.000 1.2121 0.02519 0.01658 -0.0554 0.0144 1.0000
9.250 1.2207 0.02630 0.01784 -0.0531 0.0139 1.0000
9.500 1.2280 0.02754 0.01922 -0.0508 0.0135 1.0000
9.750 1.2344 0.02891 0.02072 -0.0487 0.0132 1.0000
10.000 1.2392 0.03050 0.02244 -0.0467 0.0129 1.0000
10.250 1.2440 0.03221 0.02427 -0.0450 0.0126 1.0000
10.500 1.2489 0.03401 0.02619 -0.0436 0.0123 1.0000
10.750 1.2539 0.03589 0.02818 -0.0423 0.0119 1.0000
11.000 1.2589 0.03786 0.03025 -0.0413 0.0115 1.0000
11.250 1.2628 0.04001 0.03251 -0.0403 0.0111 1.0000
11.500 1.2658 0.04236 0.03495 -0.0394 0.0107 1.0000
11.750 1.2688 0.04486 0.03755 -0.0385 0.0105 1.0000
12.000 1.2728 0.04738 0.04019 -0.0375 0.0103 1.0000
12.250 1.2780 0.04984 0.04279 -0.0367 0.0102 1.0000
12.500 1.2832 0.05231 0.04543 -0.0361 0.0101 1.0000
12.750 1.2872 0.05502 0.04833 -0.0356 0.0100 1.0000
13.000 1.2900 0.05792 0.05142 -0.0352 0.0099 1.0000
13.250 1.2906 0.06114 0.05486 -0.0350 0.0098 1.0000
13.500 1.2896 0.06462 0.05855 -0.0351 0.0098 1.0000
13.750 1.2859 0.06851 0.06267 -0.0354 0.0097 1.0000
14.000 1.2800 0.07277 0.06720 -0.0361 0.0097 1.0000
14.250 1.2723 0.07741 0.07207 -0.0372 0.0096 1.0000
14.500 1.2627 0.08248 0.07736 -0.0387 0.0096 1.0000
14.750 1.2512 0.08810 0.08322 -0.0408 0.0096 1.0000
15.000 1.2390 0.09408 0.08942 -0.0433 0.0096 1.0000
15.250 1.2249 0.10069 0.09625 -0.0465 0.0096 1.0000
15.500 1.2099 0.10787 0.10365 -0.0503 0.0096 1.0000
15.750 1.1947 0.11550 0.11147 -0.0546 0.0097 1.0000
16.000 1.1785 0.12378 0.11995 -0.0595 0.0097 1.0000
16.250 1.1621 0.13263 0.12897 -0.0651 0.0098 1.0000
16.500 1.1444 0.14248 0.13899 -0.0714 0.0098 1.0000
16.750 1.1267 0.15304 0.14968 -0.0783 0.0099 1.0000
17.000 1.1079 0.16487 0.16162 -0.0858 0.0100 1.0000
17.250 1.0872 0.17837 0.17520 -0.0940 0.0102 1.0000
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Polar data table (+)
Polar graphs
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