E387 (e387-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E387 (e387-il) Reynolds number: 500,000 Max Cl/Cd: 109.14 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e387-il-500000-n5.txt Download as CSV file: xf-e387-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3475 0.09135 0.08914 -0.0306 1.0000 0.0110
-8.500 -0.3438 0.08824 0.08605 -0.0317 1.0000 0.0110
-8.250 -0.3418 0.08462 0.08247 -0.0333 1.0000 0.0111
-7.750 -0.3061 0.07144 0.06917 -0.0496 0.9104 0.0074
-7.500 -0.3043 0.06787 0.06544 -0.0524 0.8627 0.0072
-7.250 -0.3037 0.06277 0.06022 -0.0570 0.8321 0.0073
-7.000 -0.2972 0.05835 0.05568 -0.0615 0.8101 0.0071
-6.750 -0.2887 0.05188 0.04907 -0.0677 0.7925 0.0072
-6.500 -0.2765 0.04518 0.04216 -0.0730 0.7781 0.0070
-6.250 -0.2631 0.03675 0.03338 -0.0775 0.7661 0.0070
-6.000 -0.2499 0.02691 0.02287 -0.0800 0.7558 0.0070
-5.750 -0.2292 0.02243 0.01774 -0.0805 0.7456 0.0074
-5.500 -0.2047 0.02055 0.01540 -0.0804 0.7356 0.0076
-5.250 -0.1803 0.01850 0.01293 -0.0803 0.7259 0.0077
-5.000 -0.1549 0.01694 0.01103 -0.0802 0.7170 0.0077
-4.500 -0.1031 0.01408 0.00756 -0.0798 0.7005 0.0078
-4.250 -0.0769 0.01302 0.00629 -0.0796 0.6927 0.0080
-4.000 -0.0501 0.01223 0.00538 -0.0794 0.6851 0.0082
-3.750 -0.0232 0.01166 0.00469 -0.0793 0.6782 0.0086
-3.500 0.0041 0.01118 0.00413 -0.0792 0.6711 0.0090
-3.250 0.0314 0.01080 0.00364 -0.0790 0.6646 0.0096
-3.000 0.0591 0.01045 0.00321 -0.0790 0.6581 0.0102
-2.750 0.0867 0.01021 0.00288 -0.0789 0.6519 0.0109
-2.500 0.1144 0.00990 0.00249 -0.0788 0.6459 0.0123
-2.250 0.1423 0.00968 0.00221 -0.0788 0.6398 0.0134
-2.000 0.1702 0.00952 0.00196 -0.0787 0.6344 0.0153
-1.750 0.1981 0.00927 0.00177 -0.0787 0.6285 0.0306
-1.500 0.2257 0.00902 0.00163 -0.0787 0.6230 0.0728
-1.250 0.2533 0.00877 0.00154 -0.0788 0.6179 0.1265
-1.000 0.2810 0.00853 0.00148 -0.0789 0.6123 0.1894
-0.750 0.3083 0.00829 0.00143 -0.0790 0.6071 0.2716
-0.500 0.3357 0.00798 0.00141 -0.0791 0.6020 0.3740
-0.250 0.3625 0.00763 0.00142 -0.0791 0.5967 0.5045
0.000 0.3886 0.00733 0.00144 -0.0788 0.5918 0.6255
0.250 0.4140 0.00702 0.00147 -0.0782 0.5867 0.7397
0.500 0.4351 0.00668 0.00151 -0.0764 0.5817 0.8761
0.750 0.4753 0.00659 0.00146 -0.0788 0.5766 1.0000
1.000 0.5031 0.00665 0.00148 -0.0788 0.5713 1.0000
1.250 0.5308 0.00672 0.00150 -0.0787 0.5661 1.0000
1.500 0.5584 0.00680 0.00153 -0.0787 0.5611 1.0000
1.750 0.5862 0.00687 0.00158 -0.0786 0.5555 1.0000
2.000 0.6138 0.00696 0.00162 -0.0786 0.5498 1.0000
2.250 0.6415 0.00704 0.00168 -0.0785 0.5433 1.0000
2.500 0.6689 0.00714 0.00174 -0.0785 0.5360 1.0000
2.750 0.6965 0.00722 0.00182 -0.0784 0.5283 1.0000
3.000 0.7237 0.00734 0.00189 -0.0783 0.5197 1.0000
3.250 0.7512 0.00743 0.00198 -0.0783 0.5104 1.0000
3.500 0.7785 0.00754 0.00209 -0.0782 0.5015 1.0000
4.000 0.8327 0.00780 0.00231 -0.0780 0.4799 1.0000
4.250 0.8596 0.00794 0.00244 -0.0779 0.4673 1.0000
4.500 0.8862 0.00812 0.00260 -0.0777 0.4512 1.0000
4.750 0.9120 0.00836 0.00276 -0.0774 0.4256 1.0000
5.000 0.9365 0.00875 0.00298 -0.0770 0.3856 1.0000
5.250 0.9579 0.00949 0.00336 -0.0762 0.3130 1.0000
5.500 0.9777 0.01046 0.00393 -0.0753 0.2343 1.0000
5.750 0.9993 0.01121 0.00443 -0.0746 0.1834 1.0000
6.250 1.0416 0.01273 0.00549 -0.0731 0.0944 1.0000
6.500 1.0620 0.01354 0.00610 -0.0722 0.0571 1.0000
6.750 1.0824 0.01431 0.00672 -0.0713 0.0302 1.0000
7.000 1.1023 0.01511 0.00741 -0.0703 0.0126 1.0000
7.250 1.1246 0.01563 0.00796 -0.0696 0.0106 1.0000
7.500 1.1469 0.01613 0.00853 -0.0689 0.0098 1.0000
7.750 1.1686 0.01665 0.00912 -0.0681 0.0093 1.0000
8.000 1.1896 0.01722 0.00977 -0.0672 0.0089 1.0000
8.250 1.2096 0.01786 0.01048 -0.0662 0.0084 1.0000
8.500 1.2284 0.01855 0.01124 -0.0650 0.0080 1.0000
8.750 1.2454 0.01936 0.01212 -0.0636 0.0076 1.0000
9.000 1.2593 0.02035 0.01322 -0.0619 0.0072 1.0000
9.250 1.2715 0.02138 0.01434 -0.0599 0.0070 1.0000
9.500 1.2826 0.02226 0.01531 -0.0576 0.0069 1.0000
9.750 1.2922 0.02316 0.01629 -0.0553 0.0068 1.0000
10.000 1.2997 0.02424 0.01746 -0.0529 0.0067 1.0000
10.250 1.3069 0.02542 0.01872 -0.0507 0.0066 1.0000
10.500 1.3131 0.02675 0.02015 -0.0486 0.0065 1.0000
10.750 1.3190 0.02822 0.02173 -0.0468 0.0064 1.0000
11.000 1.3246 0.02981 0.02343 -0.0453 0.0063 1.0000
11.250 1.3294 0.03158 0.02530 -0.0438 0.0062 1.0000
11.500 1.3346 0.03341 0.02724 -0.0426 0.0060 1.0000
11.750 1.3385 0.03546 0.02940 -0.0415 0.0060 1.0000
12.000 1.3427 0.03755 0.03161 -0.0406 0.0059 1.0000
12.250 1.3464 0.03978 0.03395 -0.0397 0.0058 1.0000
12.500 1.3500 0.04207 0.03636 -0.0391 0.0056 1.0000
12.750 1.3524 0.04458 0.03900 -0.0385 0.0056 1.0000
13.000 1.3545 0.04719 0.04175 -0.0380 0.0055 1.0000
13.250 1.3562 0.04988 0.04456 -0.0378 0.0054 1.0000
13.500 1.3571 0.05274 0.04755 -0.0377 0.0054 1.0000
13.750 1.3571 0.05577 0.05072 -0.0378 0.0052 1.0000
14.000 1.3563 0.05895 0.05401 -0.0381 0.0051 1.0000
14.250 1.3541 0.06247 0.05767 -0.0385 0.0051 1.0000
14.500 1.3507 0.06625 0.06159 -0.0392 0.0050 1.0000
14.750 1.3472 0.07015 0.06561 -0.0402 0.0049 1.0000
15.000 1.3425 0.07441 0.07001 -0.0413 0.0049 1.0000
15.250 1.3362 0.07909 0.07484 -0.0428 0.0048 1.0000
15.500 1.3281 0.08421 0.08011 -0.0446 0.0048 1.0000
15.750 1.3200 0.08957 0.08562 -0.0468 0.0048 1.0000
16.000 1.3099 0.09546 0.09167 -0.0493 0.0047 1.0000
16.250 1.2995 0.10166 0.09804 -0.0522 0.0047 1.0000
16.500 1.2872 0.10844 0.10498 -0.0556 0.0047 1.0000
16.750 1.2752 0.11545 0.11215 -0.0593 0.0047 1.0000
17.000 1.2628 0.12285 0.11971 -0.0635 0.0047 1.0000
17.250 1.2496 0.13069 0.12772 -0.0681 0.0047 1.0000
17.500 1.2368 0.13875 0.13593 -0.0730 0.0047 1.0000
17.750 1.2234 0.14730 0.14463 -0.0783 0.0047 1.0000
18.000 1.2097 0.15635 0.15383 -0.0840 0.0047 1.0000
18.250 1.1947 0.16619 0.16382 -0.0902 0.0047 1.0000
18.500 1.1753 0.17810 0.17590 -0.0977 0.0048 1.0000
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Polar data table (+)
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