E387 (e387-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E387 (e387-il) Reynolds number: 50,000 Max Cl/Cd: 38.66 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e387-il-50000-n5.txt Download as CSV file: xf-e387-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3401 0.09787 0.09138 -0.0300 1.0000 0.1108
-7.750 -0.3536 0.09657 0.09027 -0.0328 1.0000 0.1142
-7.500 -0.3631 0.09452 0.08838 -0.0370 1.0000 0.1149
-7.250 -0.3546 0.09031 0.08426 -0.0355 1.0000 0.1160
-7.000 -0.3471 0.08216 0.07605 -0.0407 1.0000 0.0590
-6.750 -0.3434 0.07928 0.07326 -0.0390 1.0000 0.0565
-6.500 -0.3448 0.07623 0.07032 -0.0395 1.0000 0.0543
-6.000 -0.3558 0.06783 0.06187 -0.0458 1.0000 0.0469
-5.750 -0.3445 0.06446 0.05850 -0.0469 0.9948 0.0461
-5.500 -0.3144 0.05923 0.05311 -0.0533 0.9827 0.0448
-5.250 -0.2819 0.05371 0.04732 -0.0601 0.9711 0.0435
-5.000 -0.2480 0.04825 0.04146 -0.0664 0.9596 0.0425
-4.750 -0.2141 0.04330 0.03597 -0.0714 0.9484 0.0418
-4.500 -0.1782 0.03889 0.03095 -0.0756 0.9387 0.0416
-4.250 -0.1398 0.03517 0.02656 -0.0791 0.9304 0.0427
-4.000 -0.1052 0.03232 0.02302 -0.0811 0.9203 0.0455
-3.750 -0.0682 0.02981 0.01991 -0.0830 0.9122 0.0480
-3.500 -0.0352 0.02790 0.01771 -0.0842 0.9028 0.0509
-3.250 -0.0025 0.02630 0.01579 -0.0848 0.8934 0.0550
-3.000 0.0326 0.02492 0.01417 -0.0858 0.8857 0.0645
-2.750 0.0623 0.02386 0.01295 -0.0860 0.8754 0.0805
-2.500 0.0945 0.02274 0.01184 -0.0869 0.8669 0.1281
-2.250 0.1247 0.02143 0.01100 -0.0876 0.8581 0.2265
-2.000 0.1498 0.02026 0.01062 -0.0874 0.8486 0.4094
-1.750 0.1687 0.01902 0.01048 -0.0841 0.8413 0.7034
-1.500 0.2178 0.01853 0.00985 -0.0872 0.8329 1.0000
-1.250 0.2476 0.01867 0.00953 -0.0875 0.8246 1.0000
-1.000 0.2740 0.01889 0.00940 -0.0873 0.8149 1.0000
-0.750 0.3006 0.01912 0.00930 -0.0872 0.8060 1.0000
-0.500 0.3288 0.01931 0.00919 -0.0872 0.7981 1.0000
-0.250 0.3537 0.01961 0.00927 -0.0868 0.7888 1.0000
0.000 0.3831 0.01979 0.00921 -0.0869 0.7821 1.0000
0.250 0.4072 0.02016 0.00940 -0.0866 0.7726 1.0000
0.500 0.4351 0.02040 0.00947 -0.0865 0.7657 1.0000
0.750 0.4600 0.02077 0.00971 -0.0862 0.7569 1.0000
1.000 0.4868 0.02107 0.00989 -0.0860 0.7498 1.0000
1.250 0.5121 0.02144 0.01017 -0.0857 0.7417 1.0000
1.500 0.5381 0.02179 0.01044 -0.0855 0.7344 1.0000
1.750 0.5636 0.02218 0.01077 -0.0852 0.7268 1.0000
2.000 0.5890 0.02257 0.01114 -0.0849 0.7194 1.0000
2.250 0.6145 0.02297 0.01151 -0.0846 0.7119 1.0000
2.500 0.6393 0.02342 0.01195 -0.0842 0.7044 1.0000
2.750 0.6648 0.02383 0.01238 -0.0839 0.6970 1.0000
3.000 0.6889 0.02433 0.01293 -0.0835 0.6893 1.0000
3.250 0.7145 0.02473 0.01337 -0.0831 0.6820 1.0000
3.500 0.7377 0.02530 0.01400 -0.0826 0.6738 1.0000
3.750 0.7640 0.02565 0.01441 -0.0822 0.6667 1.0000
4.000 0.7859 0.02629 0.01519 -0.0816 0.6575 1.0000
4.250 0.8139 0.02651 0.01548 -0.0812 0.6508 1.0000
4.500 0.8344 0.02719 0.01631 -0.0804 0.6403 1.0000
4.750 0.8589 0.02761 0.01689 -0.0798 0.6315 1.0000
5.000 0.8847 0.02787 0.01729 -0.0791 0.6225 1.0000
5.250 0.9059 0.02843 0.01801 -0.0781 0.6111 1.0000
5.500 0.9292 0.02879 0.01855 -0.0772 0.6000 1.0000
5.750 0.9549 0.02891 0.01887 -0.0762 0.5890 1.0000
6.000 0.9817 0.02886 0.01900 -0.0752 0.5774 1.0000
6.250 1.0046 0.02902 0.01937 -0.0739 0.5634 1.0000
6.500 1.0277 0.02907 0.01962 -0.0725 0.5481 1.0000
6.750 1.0469 0.02932 0.02017 -0.0709 0.5301 1.0000
7.000 1.0681 0.02930 0.02039 -0.0691 0.5108 1.0000
7.250 1.0905 0.02906 0.02036 -0.0673 0.4897 1.0000
7.500 1.1089 0.02907 0.02060 -0.0652 0.4642 1.0000
7.750 1.1256 0.02915 0.02086 -0.0629 0.4337 1.0000
8.000 1.1388 0.02946 0.02135 -0.0603 0.3947 1.0000
8.250 1.1488 0.03001 0.02183 -0.0574 0.3439 1.0000
8.500 1.1526 0.03118 0.02265 -0.0542 0.2846 1.0000
8.750 1.1482 0.03318 0.02422 -0.0509 0.2301 1.0000
9.000 1.1384 0.03567 0.02632 -0.0478 0.1850 1.0000
9.250 1.1292 0.03854 0.02887 -0.0456 0.1459 1.0000
9.500 1.1210 0.04168 0.03170 -0.0441 0.1150 1.0000
9.750 1.1165 0.04476 0.03467 -0.0430 0.0928 1.0000
10.000 1.1109 0.04813 0.03791 -0.0420 0.0775 1.0000
10.250 1.1088 0.05128 0.04106 -0.0411 0.0665 1.0000
10.500 1.1092 0.05427 0.04411 -0.0402 0.0584 1.0000
10.750 1.1095 0.05729 0.04715 -0.0396 0.0530 1.0000
11.000 1.1149 0.05988 0.04995 -0.0387 0.0478 1.0000
11.250 1.1194 0.06259 0.05271 -0.0379 0.0446 1.0000
11.500 1.1311 0.06479 0.05506 -0.0364 0.0422 1.0000
11.750 1.1489 0.06680 0.05742 -0.0345 0.0398 1.0000
12.000 1.1636 0.06933 0.06026 -0.0332 0.0381 1.0000
12.250 1.1712 0.07249 0.06367 -0.0326 0.0367 1.0000
12.500 1.1742 0.07599 0.06740 -0.0325 0.0355 1.0000
12.750 1.1751 0.07973 0.07128 -0.0326 0.0344 1.0000
13.000 1.1731 0.08408 0.07584 -0.0330 0.0336 1.0000
13.250 1.1624 0.08934 0.08144 -0.0345 0.0333 1.0000
13.500 1.1500 0.09502 0.08741 -0.0365 0.0331 1.0000
13.750 1.1355 0.10126 0.09391 -0.0392 0.0331 1.0000
14.000 1.1196 0.10802 0.10091 -0.0425 0.0331 1.0000
14.250 1.1037 0.11523 0.10827 -0.0464 0.0332 1.0000
14.500 1.0875 0.12306 0.11627 -0.0510 0.0334 1.0000
14.750 1.0717 0.13143 0.12477 -0.0560 0.0336 1.0000
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