E387 (e387-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E387 (e387-il) Reynolds number: 500,000 Max Cl/Cd: 116.26 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e387-il-500000.txt Download as CSV file: xf-e387-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2755 0.09944 0.09734 -0.0275 1.0000 0.0161
-9.750 -0.2761 0.09551 0.09343 -0.0297 1.0000 0.0164
-9.500 -0.2740 0.09170 0.08964 -0.0313 1.0000 0.0165
-9.250 -0.2715 0.08789 0.08584 -0.0327 1.0000 0.0166
-9.000 -0.2697 0.08401 0.08199 -0.0340 1.0000 0.0166
-8.750 -0.2681 0.08010 0.07810 -0.0353 1.0000 0.0167
-8.500 -0.2668 0.07627 0.07429 -0.0365 1.0000 0.0167
-8.250 -0.2709 0.07122 0.06928 -0.0366 1.0000 0.0172
-8.000 -0.2685 0.06812 0.06621 -0.0369 1.0000 0.0175
-7.750 -0.2649 0.06476 0.06288 -0.0380 0.9965 0.0177
-7.500 -0.2490 0.06005 0.05816 -0.0428 0.9732 0.0183
-7.250 -0.2338 0.05491 0.05299 -0.0485 0.9442 0.0190
-7.000 -0.2326 0.05092 0.04891 -0.0512 0.9027 0.0192
-6.750 -0.2345 0.04716 0.04505 -0.0537 0.8719 0.0197
-6.500 -0.2321 0.04249 0.04027 -0.0582 0.8495 0.0203
-6.250 -0.2252 0.03708 0.03473 -0.0634 0.8320 0.0210
-5.750 -0.1959 0.03910 0.03595 -0.0814 0.8468 0.0226
-5.500 -0.1869 0.03291 0.02951 -0.0832 0.8293 0.0239
-5.250 -0.1664 0.03132 0.02777 -0.0834 0.8137 0.0250
-5.000 -0.1439 0.02900 0.02519 -0.0837 0.7997 0.0273
-4.750 -0.1204 0.02501 0.02047 -0.0839 0.7876 0.0316
-4.500 -0.0971 0.02304 0.01842 -0.0841 0.7759 0.0331
-4.250 -0.0721 0.02166 0.01684 -0.0840 0.7655 0.0353
-4.000 -0.0441 0.01475 0.00875 -0.0824 0.7570 0.0189
-3.750 -0.0164 0.01341 0.00704 -0.0817 0.7476 0.0171
-3.500 0.0106 0.01269 0.00615 -0.0814 0.7390 0.0168
-3.250 0.0376 0.01174 0.00508 -0.0811 0.7301 0.0168
-3.000 0.0640 0.01075 0.00395 -0.0807 0.7224 0.0174
-2.750 0.0912 0.01019 0.00332 -0.0806 0.7143 0.0187
-2.500 0.1189 0.00987 0.00291 -0.0804 0.7070 0.0207
-2.250 0.1467 0.00957 0.00253 -0.0803 0.6996 0.0237
-2.000 0.1744 0.00921 0.00217 -0.0801 0.6930 0.0423
-1.750 0.2016 0.00871 0.00199 -0.0802 0.6859 0.1316
-1.500 0.2288 0.00840 0.00189 -0.0803 0.6799 0.2173
-1.250 0.2557 0.00795 0.00185 -0.0804 0.6731 0.3486
-1.000 0.2815 0.00746 0.00184 -0.0802 0.6673 0.5223
-0.750 0.3054 0.00689 0.00188 -0.0794 0.6611 0.7155
-0.500 0.3249 0.00646 0.00190 -0.0771 0.6554 0.8836
-0.250 0.3698 0.00636 0.00179 -0.0805 0.6495 1.0000
0.000 0.3973 0.00642 0.00177 -0.0804 0.6435 1.0000
0.250 0.4246 0.00652 0.00175 -0.0802 0.6381 1.0000
0.500 0.4523 0.00657 0.00176 -0.0802 0.6322 1.0000
0.750 0.4799 0.00665 0.00176 -0.0801 0.6267 1.0000
1.000 0.5075 0.00675 0.00179 -0.0800 0.6214 1.0000
1.250 0.5352 0.00681 0.00182 -0.0800 0.6155 1.0000
1.500 0.5628 0.00691 0.00185 -0.0799 0.6102 1.0000
1.750 0.5905 0.00699 0.00192 -0.0798 0.6044 1.0000
2.000 0.6181 0.00706 0.00196 -0.0798 0.5984 1.0000
2.250 0.6456 0.00717 0.00202 -0.0797 0.5925 1.0000
2.500 0.6732 0.00723 0.00208 -0.0796 0.5856 1.0000
2.750 0.7006 0.00735 0.00216 -0.0795 0.5791 1.0000
3.000 0.7281 0.00740 0.00223 -0.0795 0.5713 1.0000
3.250 0.7553 0.00752 0.00230 -0.0794 0.5644 1.0000
3.500 0.7828 0.00758 0.00239 -0.0793 0.5563 1.0000
3.750 0.8100 0.00769 0.00250 -0.0792 0.5487 1.0000
4.000 0.8372 0.00777 0.00260 -0.0790 0.5400 1.0000
4.250 0.8644 0.00787 0.00271 -0.0789 0.5311 1.0000
4.500 0.8913 0.00799 0.00282 -0.0788 0.5217 1.0000
4.750 0.9183 0.00808 0.00296 -0.0786 0.5113 1.0000
5.000 0.9450 0.00820 0.00309 -0.0784 0.4982 1.0000
5.250 0.9708 0.00835 0.00320 -0.0781 0.4750 1.0000
5.500 0.9961 0.00857 0.00335 -0.0777 0.4474 1.0000
5.750 1.0213 0.00883 0.00357 -0.0773 0.4217 1.0000
6.000 1.0454 0.00921 0.00383 -0.0768 0.3840 1.0000
6.250 1.0660 0.00997 0.00426 -0.0759 0.3148 1.0000
6.500 1.0838 0.01105 0.00492 -0.0747 0.2350 1.0000
6.750 1.1018 0.01212 0.00563 -0.0735 0.1679 1.0000
7.000 1.1190 0.01323 0.00639 -0.0723 0.1069 1.0000
7.250 1.1337 0.01456 0.00732 -0.0707 0.0462 1.0000
7.500 1.1498 0.01571 0.00828 -0.0691 0.0194 1.0000
7.750 1.1705 0.01635 0.00900 -0.0681 0.0169 1.0000
8.000 1.1893 0.01714 0.00984 -0.0668 0.0151 1.0000
8.250 1.2061 0.01806 0.01087 -0.0652 0.0141 1.0000
8.500 1.2241 0.01881 0.01171 -0.0639 0.0135 1.0000
8.750 1.2395 0.01970 0.01269 -0.0622 0.0131 1.0000
9.000 1.2535 0.02064 0.01372 -0.0604 0.0127 1.0000
9.250 1.2641 0.02168 0.01487 -0.0580 0.0124 1.0000
9.500 1.2712 0.02275 0.01602 -0.0552 0.0120 1.0000
9.750 1.2773 0.02394 0.01729 -0.0525 0.0118 1.0000
10.000 1.2827 0.02526 0.01872 -0.0499 0.0117 1.0000
10.250 1.2879 0.02674 0.02027 -0.0477 0.0114 1.0000
10.500 1.2932 0.02836 0.02200 -0.0456 0.0114 1.0000
10.750 1.2985 0.03012 0.02384 -0.0438 0.0111 1.0000
11.000 1.3049 0.03197 0.02578 -0.0421 0.0110 1.0000
11.250 1.3125 0.03386 0.02779 -0.0406 0.0110 1.0000
11.500 1.3206 0.03591 0.02996 -0.0392 0.0108 1.0000
11.750 1.3291 0.03824 0.03240 -0.0379 0.0106 1.0000
12.000 1.3393 0.04141 0.03574 -0.0366 0.0103 1.0000
12.250 1.3467 0.04359 0.03807 -0.0355 0.0103 1.0000
12.500 1.3516 0.04632 0.04099 -0.0344 0.0103 1.0000
12.750 1.3536 0.04922 0.04409 -0.0335 0.0104 1.0000
13.000 1.3536 0.05204 0.04709 -0.0327 0.0104 1.0000
13.250 1.3506 0.05530 0.05055 -0.0322 0.0105 1.0000
13.500 1.3452 0.05887 0.05432 -0.0319 0.0105 1.0000
13.750 1.3354 0.06304 0.05880 -0.0320 0.0109 1.0000
14.000 1.2859 0.07440 0.07086 -0.0336 0.0125 1.0000
14.250 1.2621 0.08158 0.07828 -0.0358 0.0130 1.0000
14.500 1.2408 0.08850 0.08540 -0.0386 0.0132 1.0000
14.750 1.2188 0.09609 0.09316 -0.0422 0.0135 1.0000
15.000 1.0686 0.10057 0.09795 -0.0423 0.0120 1.0000
15.250 1.0383 0.10856 0.10615 -0.0471 0.0122 1.0000
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Polar data table (+)
Polar graphs
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