EPPLER 587 AIRFOIL (e587-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 587 AIRFOIL (e587-il) Reynolds number: 500,000 Max Cl/Cd: 109.96 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e587-il-500000-n5.txt Download as CSV file: xf-e587-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3804 0.05414 0.05118 -0.1272 0.9393 0.0040
-12.250 -0.3954 0.04364 0.04025 -0.1402 0.9307 0.0040
-12.000 -0.3886 0.03710 0.03330 -0.1503 0.9203 0.0040
-11.750 -0.3751 0.03265 0.02843 -0.1571 0.9059 0.0041
-11.500 -0.3647 0.02974 0.02518 -0.1601 0.8888 0.0042
-11.250 -0.3577 0.02777 0.02291 -0.1605 0.8732 0.0043
-11.000 -0.3524 0.02620 0.02113 -0.1598 0.8596 0.0042
-10.750 -0.3448 0.02495 0.01965 -0.1587 0.8483 0.0043
-10.500 -0.3409 0.02351 0.01800 -0.1570 0.8376 0.0044
-10.250 -0.3360 0.02227 0.01661 -0.1551 0.8288 0.0046
-10.000 -0.3279 0.02134 0.01554 -0.1533 0.8211 0.0046
-9.750 -0.3201 0.02059 0.01469 -0.1512 0.8139 0.0048
-9.500 -0.3097 0.01991 0.01389 -0.1494 0.8071 0.0049
-9.250 -0.2957 0.01912 0.01298 -0.1481 0.8015 0.0049
-9.000 -0.2788 0.01855 0.01232 -0.1471 0.7963 0.0051
-8.750 -0.2617 0.01790 0.01156 -0.1461 0.7912 0.0052
-8.500 -0.2429 0.01733 0.01088 -0.1452 0.7867 0.0055
-8.250 -0.2241 0.01673 0.01019 -0.1443 0.7821 0.0056
-8.000 -0.2043 0.01617 0.00955 -0.1436 0.7776 0.0059
-7.750 -0.1834 0.01566 0.00894 -0.1429 0.7738 0.0061
-7.500 -0.1616 0.01520 0.00839 -0.1424 0.7702 0.0062
-7.250 -0.1404 0.01466 0.00780 -0.1419 0.7662 0.0065
-7.000 -0.1176 0.01424 0.00734 -0.1415 0.7622 0.0069
-6.750 -0.0936 0.01391 0.00696 -0.1413 0.7587 0.0074
-6.500 -0.0690 0.01358 0.00654 -0.1412 0.7556 0.0082
-6.250 -0.0448 0.01319 0.00612 -0.1410 0.7523 0.0088
-6.000 -0.0200 0.01283 0.00574 -0.1409 0.7486 0.0097
-5.750 0.0055 0.01252 0.00537 -0.1408 0.7452 0.0108
-5.500 0.0313 0.01220 0.00501 -0.1409 0.7421 0.0129
-5.000 0.0842 0.01161 0.00442 -0.1412 0.7360 0.0238
-4.750 0.1108 0.01132 0.00417 -0.1414 0.7326 0.0364
-4.500 0.1379 0.01104 0.00395 -0.1417 0.7294 0.0531
-4.250 0.1653 0.01074 0.00373 -0.1422 0.7264 0.0798
-4.000 0.1931 0.01037 0.00351 -0.1428 0.7235 0.1256
-3.750 0.2211 0.00990 0.00329 -0.1436 0.7204 0.1946
-3.500 0.2498 0.00933 0.00304 -0.1447 0.7172 0.2920
-3.250 0.2799 0.00864 0.00276 -0.1462 0.7139 0.4210
-3.000 0.3098 0.00829 0.00274 -0.1472 0.7108 0.5332
-2.750 0.3390 0.00829 0.00276 -0.1476 0.7079 0.5686
-2.500 0.3678 0.00832 0.00278 -0.1479 0.7049 0.5874
-2.250 0.3964 0.00836 0.00279 -0.1482 0.7015 0.5999
-2.000 0.4251 0.00841 0.00280 -0.1485 0.6981 0.6113
-1.750 0.4535 0.00849 0.00286 -0.1486 0.6948 0.6236
-1.500 0.4819 0.00860 0.00294 -0.1488 0.6918 0.6356
-1.250 0.5105 0.00868 0.00298 -0.1491 0.6886 0.6437
-1.000 0.5387 0.00870 0.00298 -0.1493 0.6849 0.6470
-0.750 0.5667 0.00873 0.00299 -0.1495 0.6813 0.6492
-0.500 0.5949 0.00877 0.00299 -0.1497 0.6777 0.6514
-0.250 0.6232 0.00881 0.00299 -0.1500 0.6743 0.6536
0.000 0.6510 0.00884 0.00301 -0.1501 0.6702 0.6560
0.250 0.6789 0.00887 0.00303 -0.1503 0.6660 0.6584
0.500 0.7068 0.00892 0.00303 -0.1505 0.6618 0.6606
0.750 0.7347 0.00898 0.00305 -0.1507 0.6579 0.6625
1.000 0.7618 0.00900 0.00310 -0.1508 0.6532 0.6643
1.250 0.7888 0.00905 0.00314 -0.1507 0.6483 0.6663
1.750 0.8426 0.00916 0.00325 -0.1507 0.6384 0.6705
2.000 0.8691 0.00922 0.00330 -0.1506 0.6327 0.6725
2.250 0.8956 0.00930 0.00335 -0.1506 0.6276 0.6746
2.500 0.9221 0.00936 0.00343 -0.1505 0.6218 0.6768
2.750 0.9482 0.00945 0.00350 -0.1504 0.6157 0.6790
3.000 0.9736 0.00953 0.00359 -0.1501 0.6096 0.6810
3.250 0.9985 0.00960 0.00369 -0.1497 0.6021 0.6829
3.500 1.0229 0.00971 0.00380 -0.1492 0.5947 0.6848
3.750 1.0472 0.00981 0.00391 -0.1487 0.5864 0.6869
4.000 1.0710 0.00994 0.00403 -0.1481 0.5786 0.6891
4.250 1.0944 0.01007 0.00417 -0.1474 0.5696 0.6914
4.500 1.1172 0.01021 0.00431 -0.1466 0.5608 0.6939
4.750 1.1380 0.01038 0.00446 -0.1454 0.5504 0.6962
5.000 1.1579 0.01053 0.00463 -0.1441 0.5392 0.6982
5.250 1.1762 0.01072 0.00481 -0.1424 0.5273 0.7003
5.500 1.1933 0.01095 0.00503 -0.1405 0.5146 0.7025
5.750 1.2099 0.01124 0.00530 -0.1385 0.5005 0.7049
6.000 1.2257 0.01157 0.00559 -0.1365 0.4855 0.7075
6.250 1.2410 0.01193 0.00591 -0.1344 0.4701 0.7102
6.500 1.2555 0.01233 0.00627 -0.1322 0.4537 0.7128
6.750 1.2686 0.01277 0.00669 -0.1298 0.4362 0.7153
7.000 1.2807 0.01327 0.00716 -0.1272 0.4179 0.7178
7.250 1.2926 0.01381 0.00766 -0.1248 0.4004 0.7205
7.500 1.3031 0.01442 0.00823 -0.1221 0.3822 0.7233
7.750 1.3134 0.01509 0.00885 -0.1196 0.3647 0.7262
8.250 1.3318 0.01661 0.01029 -0.1144 0.3297 0.7320
8.500 1.3405 0.01746 0.01110 -0.1119 0.3125 0.7352
8.750 1.3492 0.01835 0.01197 -0.1095 0.2952 0.7386
9.000 1.3572 0.01934 0.01291 -0.1071 0.2774 0.7420
9.500 1.3735 0.02143 0.01494 -0.1027 0.2445 0.7484
9.750 1.3811 0.02257 0.01606 -0.1006 0.2287 0.7520
10.000 1.3879 0.02381 0.01727 -0.0985 0.2124 0.7560
10.250 1.3949 0.02510 0.01852 -0.0965 0.1968 0.7603
10.500 1.4011 0.02648 0.01987 -0.0946 0.1805 0.7644
10.750 1.4076 0.02789 0.02125 -0.0927 0.1656 0.7689
11.000 1.4138 0.02937 0.02270 -0.0910 0.1513 0.7737
11.500 1.4277 0.03234 0.02567 -0.0879 0.1269 0.7833
11.750 1.4342 0.03394 0.02726 -0.0864 0.1160 0.7890
12.000 1.4401 0.03563 0.02895 -0.0850 0.1050 0.7948
12.250 1.4453 0.03740 0.03072 -0.0836 0.0939 0.8013
12.500 1.4510 0.03919 0.03253 -0.0824 0.0839 0.8089
12.750 1.4562 0.04106 0.03441 -0.0812 0.0740 0.8172
13.250 1.4651 0.04505 0.03846 -0.0789 0.0572 0.8374
13.500 1.4692 0.04712 0.04057 -0.0779 0.0503 0.8505
13.750 1.4714 0.04941 0.04290 -0.0768 0.0428 0.8682
14.000 1.4747 0.05139 0.04499 -0.0755 0.0380 0.9041
14.250 1.4763 0.05350 0.04718 -0.0744 0.0334 1.0000
14.500 1.4797 0.05601 0.04970 -0.0739 0.0290 1.0000
14.750 1.4819 0.05870 0.05240 -0.0734 0.0241 1.0000
15.000 1.4856 0.06129 0.05503 -0.0731 0.0212 1.0000
15.250 1.4888 0.06399 0.05778 -0.0729 0.0184 1.0000
15.500 1.4909 0.06685 0.06069 -0.0728 0.0157 1.0000
15.750 1.4927 0.06982 0.06371 -0.0727 0.0137 1.0000
16.000 1.4945 0.07287 0.06682 -0.0728 0.0117 1.0000
16.250 1.4965 0.07593 0.06996 -0.0730 0.0104 1.0000
16.500 1.4982 0.07910 0.07320 -0.0732 0.0093 1.0000
16.750 1.4990 0.08245 0.07663 -0.0736 0.0083 1.0000
17.000 1.4999 0.08582 0.08008 -0.0741 0.0074 1.0000
17.250 1.4996 0.08940 0.08374 -0.0748 0.0066 1.0000
17.500 1.4996 0.09301 0.08745 -0.0755 0.0060 1.0000
17.750 1.4986 0.09682 0.09135 -0.0764 0.0054 1.0000
18.000 1.4971 0.10075 0.09537 -0.0774 0.0050 1.0000
18.250 1.4960 0.10464 0.09937 -0.0785 0.0046 1.0000
18.500 1.4940 0.10873 0.10356 -0.0797 0.0042 1.0000
18.750 1.4910 0.11301 0.10794 -0.0812 0.0039 1.0000
19.000 1.4877 0.11738 0.11242 -0.0827 0.0036 1.0000
19.250 1.4851 0.12167 0.11681 -0.0844 0.0034 1.0000
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