EPPLER 587 AIRFOIL (e587-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: EPPLER 587 AIRFOIL (e587-il) Reynolds number: 500,000 Max Cl/Cd: 116.36 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e587-il-500000.txt Download as CSV file: xf-e587-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2345 0.03001 0.02565 -0.1605 0.8707 0.0106
-9.250 -0.2337 0.02799 0.02341 -0.1585 0.8611 0.0103
-9.000 -0.2319 0.02518 0.02018 -0.1563 0.8531 0.0099
-8.750 -0.2255 0.02266 0.01727 -0.1541 0.8456 0.0095
-8.500 -0.2102 0.02105 0.01538 -0.1528 0.8395 0.0097
-8.250 -0.1910 0.01975 0.01383 -0.1520 0.8345 0.0099
-8.000 -0.1725 0.01873 0.01262 -0.1508 0.8291 0.0104
-7.750 -0.1515 0.01788 0.01160 -0.1500 0.8242 0.0107
-7.500 -0.1276 0.01725 0.01078 -0.1497 0.8199 0.0109
-7.250 -0.1102 0.01616 0.00968 -0.1484 0.8151 0.0113
-7.000 -0.0897 0.01553 0.00902 -0.1476 0.8106 0.0117
-6.750 -0.0671 0.01499 0.00843 -0.1472 0.8066 0.0122
-6.500 -0.0432 0.01454 0.00789 -0.1470 0.8028 0.0131
-6.250 -0.0220 0.01404 0.00736 -0.1462 0.7985 0.0141
-6.000 0.0007 0.01354 0.00685 -0.1459 0.7944 0.0153
-5.750 0.0256 0.01315 0.00638 -0.1458 0.7909 0.0168
-5.250 0.0749 0.01215 0.00534 -0.1456 0.7837 0.0252
-5.000 0.0995 0.01158 0.00489 -0.1456 0.7798 0.0468
-4.750 0.1260 0.01113 0.00458 -0.1460 0.7764 0.0821
-4.500 0.1537 0.01066 0.00429 -0.1467 0.7732 0.1362
-4.250 0.1811 0.00994 0.00399 -0.1478 0.7699 0.2470
-4.000 0.2090 0.00866 0.00359 -0.1497 0.7663 0.4855
-3.750 0.2378 0.00857 0.00370 -0.1501 0.7629 0.5710
-3.500 0.2673 0.00865 0.00373 -0.1505 0.7596 0.5974
-3.250 0.2974 0.00878 0.00377 -0.1509 0.7566 0.6135
-3.000 0.3260 0.00893 0.00388 -0.1511 0.7534 0.6267
-2.750 0.3533 0.00905 0.00399 -0.1509 0.7498 0.6364
-2.500 0.3823 0.00917 0.00402 -0.1512 0.7463 0.6457
-2.250 0.4105 0.00926 0.00411 -0.1513 0.7432 0.6519
-2.000 0.4403 0.00942 0.00419 -0.1517 0.7401 0.6598
-1.750 0.4673 0.00957 0.00435 -0.1514 0.7368 0.6675
-1.500 0.4942 0.00973 0.00451 -0.1512 0.7332 0.6757
-1.250 0.5222 0.00980 0.00455 -0.1513 0.7296 0.6814
-1.000 0.5504 0.00986 0.00459 -0.1514 0.7264 0.6850
-0.750 0.5805 0.00995 0.00461 -0.1520 0.7232 0.6881
-0.500 0.6074 0.00995 0.00461 -0.1520 0.7195 0.6910
-0.250 0.6357 0.00996 0.00459 -0.1523 0.7156 0.6938
0.000 0.6648 0.00996 0.00453 -0.1528 0.7118 0.6963
0.250 0.6938 0.00996 0.00450 -0.1532 0.7084 0.6982
0.500 0.7213 0.00999 0.00454 -0.1533 0.7046 0.7001
0.750 0.7479 0.01000 0.00456 -0.1533 0.7003 0.7023
1.000 0.7759 0.01001 0.00456 -0.1535 0.6962 0.7047
1.250 0.8053 0.01004 0.00454 -0.1540 0.6924 0.7071
1.500 0.8326 0.01008 0.00457 -0.1541 0.6880 0.7095
1.750 0.8597 0.01009 0.00459 -0.1542 0.6831 0.7118
2.000 0.8873 0.01007 0.00456 -0.1543 0.6787 0.7139
2.250 0.9159 0.01012 0.00459 -0.1547 0.6746 0.7160
2.500 0.9407 0.01013 0.00467 -0.1542 0.6695 0.7181
2.750 0.9672 0.01015 0.00470 -0.1542 0.6644 0.7203
3.000 0.9959 0.01021 0.00471 -0.1545 0.6597 0.7226
3.250 1.0203 0.01023 0.00479 -0.1541 0.6537 0.7251
3.500 1.0464 0.01026 0.00482 -0.1539 0.6478 0.7277
3.750 1.0735 0.01031 0.00485 -0.1540 0.6423 0.7300
4.000 1.0970 0.01033 0.00495 -0.1533 0.6358 0.7322
4.250 1.1226 0.01038 0.00500 -0.1530 0.6296 0.7343
4.500 1.1465 0.01044 0.00512 -0.1525 0.6228 0.7367
4.750 1.1705 0.01051 0.00520 -0.1519 0.6153 0.7393
5.000 1.1941 0.01059 0.00530 -0.1513 0.6076 0.7420
5.250 1.2173 0.01069 0.00540 -0.1506 0.5992 0.7448
5.500 1.2392 0.01077 0.00553 -0.1496 0.5904 0.7473
5.750 1.2604 0.01090 0.00565 -0.1484 0.5813 0.7498
6.000 1.2800 0.01101 0.00582 -0.1470 0.5706 0.7525
6.250 1.2986 0.01116 0.00599 -0.1454 0.5602 0.7553
6.500 1.3147 0.01134 0.00616 -0.1433 0.5488 0.7584
6.750 1.3303 0.01156 0.00637 -0.1411 0.5359 0.7614
7.000 1.3453 0.01180 0.00663 -0.1388 0.5223 0.7644
7.250 1.3592 0.01210 0.00695 -0.1364 0.5079 0.7676
7.500 1.3720 0.01247 0.00730 -0.1338 0.4920 0.7711
7.750 1.3837 0.01290 0.00770 -0.1311 0.4754 0.7747
8.000 1.3938 0.01342 0.00817 -0.1283 0.4574 0.7782
8.250 1.4020 0.01399 0.00872 -0.1251 0.4392 0.7816
8.500 1.4101 0.01462 0.00933 -0.1221 0.4193 0.7854
8.750 1.4169 0.01537 0.01004 -0.1189 0.3993 0.7899
9.000 1.4232 0.01622 0.01082 -0.1159 0.3801 0.7943
9.250 1.4273 0.01716 0.01173 -0.1126 0.3608 0.7987
9.500 1.4332 0.01813 0.01267 -0.1098 0.3413 0.8034
9.750 1.4385 0.01921 0.01371 -0.1070 0.3215 0.8086
10.000 1.4427 0.02038 0.01484 -0.1042 0.3025 0.8136
10.250 1.4461 0.02167 0.01609 -0.1015 0.2835 0.8194
10.500 1.4504 0.02302 0.01739 -0.0990 0.2646 0.8260
10.750 1.4551 0.02433 0.01870 -0.0967 0.2471 0.8328
11.000 1.4601 0.02573 0.02008 -0.0946 0.2305 0.8410
11.250 1.4641 0.02719 0.02154 -0.0924 0.2143 0.8497
11.500 1.4683 0.02871 0.02305 -0.0903 0.1987 0.8604
11.750 1.4718 0.03028 0.02462 -0.0883 0.1834 0.8744
12.000 1.4744 0.03182 0.02620 -0.0860 0.1691 0.8974
12.250 1.4752 0.03335 0.02778 -0.0837 0.1553 1.0000
12.500 1.4799 0.03527 0.02964 -0.0825 0.1407 1.0000
12.750 1.4844 0.03723 0.03156 -0.0813 0.1269 1.0000
13.000 1.4886 0.03926 0.03354 -0.0801 0.1141 1.0000
13.250 1.4918 0.04142 0.03566 -0.0790 0.1015 1.0000
13.500 1.4953 0.04361 0.03782 -0.0779 0.0904 1.0000
13.750 1.4974 0.04598 0.04013 -0.0769 0.0785 1.0000
14.000 1.4998 0.04839 0.04253 -0.0761 0.0695 1.0000
14.250 1.5014 0.05095 0.04507 -0.0752 0.0604 1.0000
14.500 1.5032 0.05354 0.04764 -0.0746 0.0523 1.0000
14.750 1.5040 0.05631 0.05040 -0.0740 0.0446 1.0000
15.000 1.5064 0.05899 0.05311 -0.0735 0.0392 1.0000
15.250 1.5076 0.06185 0.05599 -0.0731 0.0341 1.0000
15.500 1.5075 0.06495 0.05910 -0.0729 0.0297 1.0000
15.750 1.5084 0.06798 0.06217 -0.0727 0.0262 1.0000
16.000 1.5094 0.07106 0.06531 -0.0727 0.0230 1.0000
16.250 1.5081 0.07451 0.06880 -0.0728 0.0206 1.0000
16.500 1.5093 0.07774 0.07211 -0.0730 0.0185 1.0000
16.750 1.5073 0.08143 0.07586 -0.0734 0.0167 1.0000
17.000 1.5076 0.08485 0.07937 -0.0739 0.0151 1.0000
17.250 1.5037 0.08896 0.08354 -0.0745 0.0138 1.0000
17.500 1.5033 0.09263 0.08733 -0.0752 0.0125 1.0000
17.750 1.4996 0.09686 0.09163 -0.0762 0.0115 1.0000
18.000 1.4959 0.10114 0.09602 -0.0773 0.0105 1.0000
18.250 1.4929 0.10535 0.10033 -0.0784 0.0096 1.0000
18.500 1.4867 0.11014 0.10521 -0.0799 0.0089 1.0000
18.750 1.4824 0.11467 0.10986 -0.0815 0.0083 1.0000
19.000 1.4788 0.11914 0.11443 -0.0831 0.0076 1.0000
19.250 1.4725 0.12409 0.11947 -0.0851 0.0071 1.0000
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