EPPLER 587 AIRFOIL (e587-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: EPPLER 587 AIRFOIL (e587-il) Reynolds number: 200,000 Max Cl/Cd: 75.85 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e587-il-200000-n5.txt Download as CSV file: xf-e587-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 587 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1842 0.08943 0.08570 -0.1059 0.9370 0.0104
-11.000 -0.1842 0.08213 0.07841 -0.1118 0.9325 0.0100
-10.750 -0.2302 0.06070 0.05683 -0.1280 0.9251 0.0094
-10.500 -0.2648 0.04809 0.04373 -0.1410 0.9158 0.0091
-10.250 -0.2766 0.04230 0.03755 -0.1459 0.9040 0.0091
-10.000 -0.2816 0.03809 0.03294 -0.1484 0.8929 0.0091
-9.750 -0.2793 0.03505 0.02956 -0.1496 0.8834 0.0093
-9.500 -0.2800 0.03323 0.02748 -0.1482 0.8724 0.0095
-9.250 -0.2743 0.03090 0.02478 -0.1475 0.8646 0.0096
-9.000 -0.2646 0.02931 0.02286 -0.1464 0.8570 0.0104
-8.750 -0.2483 0.02734 0.02044 -0.1461 0.8518 0.0108
-8.500 -0.2358 0.02628 0.01926 -0.1446 0.8447 0.0114
-8.250 -0.2163 0.02514 0.01794 -0.1443 0.8393 0.0117
-8.000 -0.1945 0.02390 0.01649 -0.1440 0.8350 0.0121
-7.750 -0.1772 0.02288 0.01534 -0.1427 0.8294 0.0124
-7.500 -0.1565 0.02192 0.01422 -0.1420 0.8245 0.0128
-7.250 -0.1334 0.02095 0.01308 -0.1417 0.8206 0.0133
-7.000 -0.1149 0.02020 0.01223 -0.1405 0.8156 0.0138
-6.750 -0.0962 0.01950 0.01151 -0.1396 0.8108 0.0144
-6.500 -0.0744 0.01884 0.01077 -0.1392 0.8068 0.0155
-6.250 -0.0501 0.01820 0.00998 -0.1392 0.8035 0.0168
-6.000 -0.0312 0.01774 0.00953 -0.1381 0.7985 0.0188
-5.750 -0.0091 0.01726 0.00901 -0.1377 0.7942 0.0221
-5.500 0.0149 0.01671 0.00840 -0.1375 0.7907 0.0268
-5.250 0.0414 0.01619 0.00783 -0.1379 0.7877 0.0356
-5.000 0.0629 0.01573 0.00745 -0.1373 0.7833 0.0510
-4.750 0.0865 0.01526 0.00708 -0.1372 0.7792 0.0769
-4.500 0.1120 0.01472 0.00671 -0.1376 0.7757 0.1219
-4.250 0.1393 0.01400 0.00630 -0.1387 0.7727 0.2032
-4.000 0.1655 0.01305 0.00590 -0.1399 0.7692 0.3442
-3.750 0.1894 0.01252 0.00607 -0.1398 0.7651 0.5171
-3.500 0.2162 0.01266 0.00627 -0.1394 0.7616 0.5724
-3.250 0.2452 0.01281 0.00633 -0.1396 0.7584 0.5999
-3.000 0.2751 0.01298 0.00638 -0.1399 0.7557 0.6182
-2.750 0.3011 0.01315 0.00648 -0.1395 0.7518 0.6319
-2.500 0.3277 0.01333 0.00658 -0.1393 0.7479 0.6457
-2.250 0.3534 0.01362 0.00685 -0.1385 0.7444 0.6590
-2.000 0.3803 0.01385 0.00703 -0.1380 0.7413 0.6691
-1.750 0.4104 0.01393 0.00699 -0.1386 0.7385 0.6767
-1.500 0.4349 0.01399 0.00702 -0.1381 0.7342 0.6808
-1.250 0.4610 0.01404 0.00703 -0.1379 0.7303 0.6835
-1.000 0.4894 0.01405 0.00698 -0.1382 0.7269 0.6864
-0.750 0.5197 0.01406 0.00689 -0.1389 0.7241 0.6895
-0.500 0.5472 0.01408 0.00687 -0.1391 0.7203 0.6929
-0.250 0.5741 0.01411 0.00684 -0.1394 0.7160 0.6960
0.000 0.6009 0.01414 0.00685 -0.1393 0.7122 0.6979
0.250 0.6297 0.01415 0.00683 -0.1396 0.7089 0.7001
0.500 0.6579 0.01419 0.00684 -0.1399 0.7054 0.7024
0.750 0.6821 0.01426 0.00692 -0.1395 0.7006 0.7049
1.000 0.7096 0.01429 0.00693 -0.1397 0.6964 0.7078
1.250 0.7399 0.01430 0.00688 -0.1405 0.6928 0.7110
1.500 0.7668 0.01435 0.00692 -0.1406 0.6885 0.7133
1.750 0.7903 0.01443 0.00704 -0.1399 0.6834 0.7152
2.000 0.8173 0.01446 0.00708 -0.1399 0.6789 0.7172
2.250 0.8475 0.01447 0.00705 -0.1406 0.6752 0.7196
2.500 0.8689 0.01458 0.00723 -0.1396 0.6691 0.7226
2.750 0.8952 0.01463 0.00728 -0.1396 0.6638 0.7255
3.000 0.9260 0.01463 0.00725 -0.1404 0.6595 0.7283
3.250 0.9465 0.01475 0.00744 -0.1392 0.6529 0.7304
3.500 0.9715 0.01480 0.00752 -0.1388 0.6472 0.7325
3.750 0.9981 0.01485 0.00760 -0.1388 0.6420 0.7349
4.000 1.0192 0.01497 0.00779 -0.1377 0.6349 0.7379
4.250 1.0464 0.01500 0.00782 -0.1378 0.6290 0.7409
4.500 1.0678 0.01513 0.00802 -0.1369 0.6213 0.7440
4.750 1.0926 0.01519 0.00809 -0.1365 0.6141 0.7464
5.000 1.1127 0.01531 0.00829 -0.1352 0.6059 0.7487
5.250 1.1358 0.01539 0.00840 -0.1345 0.5981 0.7514
5.500 1.1548 0.01555 0.00863 -0.1330 0.5893 0.7547
5.750 1.1777 0.01566 0.00873 -0.1322 0.5809 0.7581
6.000 1.1936 0.01584 0.00899 -0.1302 0.5706 0.7617
6.250 1.2107 0.01601 0.00921 -0.1284 0.5605 0.7643
6.500 1.2288 0.01620 0.00941 -0.1267 0.5495 0.7672
6.750 1.2437 0.01648 0.00975 -0.1246 0.5370 0.7707
7.000 1.2595 0.01679 0.01009 -0.1227 0.5239 0.7746
7.250 1.2745 0.01714 0.01046 -0.1207 0.5101 0.7785
7.500 1.2879 0.01752 0.01087 -0.1184 0.4958 0.7820
7.750 1.3002 0.01798 0.01134 -0.1160 0.4803 0.7861
8.000 1.3116 0.01851 0.01187 -0.1136 0.4639 0.7904
8.250 1.3219 0.01913 0.01248 -0.1111 0.4468 0.7947
8.500 1.3303 0.01982 0.01317 -0.1083 0.4294 0.7987
8.750 1.3379 0.02062 0.01395 -0.1056 0.4117 0.8037
9.000 1.3453 0.02152 0.01483 -0.1030 0.3943 0.8094
9.250 1.3501 0.02251 0.01582 -0.1001 0.3765 0.8145
9.500 1.3557 0.02358 0.01688 -0.0975 0.3589 0.8204
9.750 1.3612 0.02473 0.01803 -0.0951 0.3414 0.8266
10.000 1.3651 0.02598 0.01927 -0.0925 0.3236 0.8329
10.250 1.3692 0.02733 0.02062 -0.0901 0.3061 0.8404
10.500 1.3728 0.02870 0.02201 -0.0878 0.2897 0.8485
10.750 1.3761 0.03018 0.02350 -0.0855 0.2731 0.8586
11.000 1.3787 0.03171 0.02503 -0.0833 0.2570 0.8712
11.500 1.3797 0.03470 0.02812 -0.0782 0.2274 0.9300
11.750 1.3818 0.03642 0.02984 -0.0765 0.2125 1.0000
12.000 1.3861 0.03838 0.03177 -0.0753 0.1973 1.0000
12.250 1.3900 0.04043 0.03380 -0.0742 0.1823 1.0000
12.500 1.3937 0.04254 0.03589 -0.0731 0.1680 1.0000
12.750 1.3971 0.04475 0.03808 -0.0722 0.1544 1.0000
13.000 1.4004 0.04703 0.04036 -0.0713 0.1416 1.0000
13.250 1.4035 0.04937 0.04270 -0.0705 0.1297 1.0000
13.500 1.4059 0.05185 0.04518 -0.0698 0.1185 1.0000
13.750 1.4084 0.05438 0.04771 -0.0692 0.1078 1.0000
14.000 1.4116 0.05689 0.05025 -0.0687 0.0976 1.0000
14.250 1.4137 0.05960 0.05298 -0.0682 0.0882 1.0000
14.500 1.4149 0.06247 0.05587 -0.0679 0.0795 1.0000
15.000 1.4167 0.06845 0.06192 -0.0676 0.0636 1.0000
15.250 1.4170 0.07163 0.06515 -0.0675 0.0570 1.0000
15.500 1.4157 0.07508 0.06863 -0.0677 0.0512 1.0000
15.750 1.4161 0.07837 0.07199 -0.0679 0.0458 1.0000
16.000 1.4150 0.08192 0.07562 -0.0682 0.0415 1.0000
16.250 1.4131 0.08565 0.07941 -0.0687 0.0374 1.0000
16.500 1.4118 0.08939 0.08325 -0.0693 0.0340 1.0000
16.750 1.4089 0.09342 0.08735 -0.0702 0.0310 1.0000
17.000 1.4069 0.09736 0.09141 -0.0710 0.0284 1.0000
17.250 1.4036 0.10156 0.09570 -0.0721 0.0260 1.0000
17.500 1.4001 0.10585 0.10009 -0.0734 0.0240 1.0000
17.750 1.3969 0.11015 0.10452 -0.0748 0.0222 1.0000
18.250 1.3885 0.11924 0.11382 -0.0781 0.0191 1.0000
18.500 1.3839 0.12390 0.11859 -0.0800 0.0178 1.0000
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