EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 580 AIRFOIL (e580-il) Reynolds number: 500,000 Max Cl/Cd: 107.36 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e580-il-500000.txt Download as CSV file: xf-e580-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 580 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1605 0.10002 0.09783 -0.0780 0.9842 0.0281
-11.250 -0.1748 0.09049 0.08832 -0.0841 0.9824 0.0302
-11.000 -0.2949 0.10252 0.10028 -0.0671 0.9901 0.0260
-10.750 -0.2850 0.09804 0.09580 -0.0711 0.9881 0.0266
-10.500 -0.2768 0.09262 0.09038 -0.0762 0.9863 0.0276
-9.250 -0.2892 0.03206 0.02931 -0.1242 0.9495 0.0322
-9.000 -0.2775 0.02868 0.02580 -0.1292 0.9461 0.0329
-8.750 -0.2749 0.02623 0.02321 -0.1296 0.9363 0.0337
-8.500 -0.2517 0.02533 0.02185 -0.1337 0.9326 0.0375
-7.750 -0.2451 0.02387 0.01866 -0.1374 0.9206 0.0246
-7.500 -0.2114 0.02052 0.01520 -0.1394 0.9185 0.0230
-7.250 -0.1866 0.01910 0.01364 -0.1392 0.9103 0.0229
-7.000 -0.1503 0.01779 0.01218 -0.1413 0.9059 0.0232
-6.750 -0.1189 0.01658 0.01086 -0.1423 0.8991 0.0231
-6.500 -0.0862 0.01553 0.00972 -0.1435 0.8918 0.0231
-6.250 -0.0560 0.01470 0.00881 -0.1443 0.8829 0.0233
-6.000 -0.0232 0.01396 0.00798 -0.1457 0.8744 0.0237
-5.750 0.0036 0.01340 0.00735 -0.1459 0.8633 0.0240
-5.500 0.0324 0.01290 0.00676 -0.1465 0.8531 0.0243
-5.000 0.0881 0.01162 0.00532 -0.1478 0.8316 0.0260
-4.750 0.1164 0.01127 0.00490 -0.1483 0.8212 0.0275
-4.500 0.1456 0.01098 0.00452 -0.1489 0.8114 0.0293
-4.250 0.1733 0.01073 0.00417 -0.1491 0.8005 0.0308
-4.000 0.2017 0.01043 0.00383 -0.1495 0.7905 0.0355
-3.750 0.2317 0.00986 0.00342 -0.1506 0.7810 0.0953
-3.500 0.2649 0.00802 0.00277 -0.1542 0.7708 0.4353
-3.250 0.2937 0.00806 0.00288 -0.1544 0.7614 0.5010
-3.000 0.3219 0.00821 0.00296 -0.1544 0.7519 0.5218
-2.750 0.3498 0.00833 0.00301 -0.1543 0.7424 0.5343
-2.500 0.3776 0.00860 0.00321 -0.1541 0.7337 0.5513
-2.250 0.4044 0.00887 0.00347 -0.1537 0.7243 0.5663
-2.000 0.4321 0.00914 0.00365 -0.1535 0.7160 0.5768
-1.750 0.4586 0.00924 0.00375 -0.1531 0.7073 0.5829
-1.500 0.4864 0.00931 0.00375 -0.1531 0.6993 0.5861
-1.250 0.5143 0.00935 0.00371 -0.1532 0.6911 0.5888
-1.000 0.5424 0.00940 0.00368 -0.1533 0.6833 0.5915
-0.750 0.5705 0.00945 0.00363 -0.1535 0.6756 0.5937
-0.500 0.5979 0.00945 0.00361 -0.1535 0.6682 0.5957
-0.250 0.6252 0.00949 0.00362 -0.1534 0.6606 0.5978
0.000 0.6528 0.00955 0.00364 -0.1534 0.6536 0.6000
0.250 0.6803 0.00960 0.00365 -0.1534 0.6463 0.6023
0.500 0.7081 0.00968 0.00366 -0.1535 0.6396 0.6046
0.750 0.7357 0.00973 0.00369 -0.1535 0.6324 0.6072
1.250 0.7905 0.00984 0.00374 -0.1536 0.6189 0.6115
1.500 0.8176 0.00992 0.00379 -0.1535 0.6123 0.6135
1.750 0.8447 0.00998 0.00386 -0.1535 0.6057 0.6156
2.000 0.8715 0.01006 0.00392 -0.1534 0.5989 0.6181
2.250 0.8987 0.01017 0.00400 -0.1533 0.5925 0.6207
2.500 0.9255 0.01024 0.00407 -0.1532 0.5855 0.6232
3.000 0.9788 0.01040 0.00422 -0.1530 0.5720 0.6276
3.250 1.0049 0.01051 0.00432 -0.1528 0.5652 0.6299
3.500 1.0309 0.01060 0.00444 -0.1525 0.5582 0.6325
3.750 1.0567 0.01071 0.00455 -0.1522 0.5510 0.6352
4.000 1.0826 0.01083 0.00468 -0.1520 0.5439 0.6379
4.250 1.1082 0.01095 0.00479 -0.1517 0.5363 0.6404
4.500 1.1334 0.01106 0.00491 -0.1513 0.5289 0.6429
4.750 1.1579 0.01117 0.00506 -0.1508 0.5206 0.6454
5.000 1.1823 0.01130 0.00522 -0.1502 0.5126 0.6484
5.250 1.2061 0.01145 0.00537 -0.1496 0.5037 0.6516
5.500 1.2301 0.01159 0.00553 -0.1490 0.4948 0.6547
5.750 1.2529 0.01179 0.00571 -0.1481 0.4859 0.6575
6.000 1.2760 0.01191 0.00589 -0.1474 0.4760 0.6604
6.250 1.2980 0.01209 0.00610 -0.1464 0.4663 0.6635
6.500 1.3183 0.01231 0.00630 -0.1451 0.4560 0.6670
6.750 1.3388 0.01249 0.00653 -0.1438 0.4450 0.6709
7.000 1.3581 0.01271 0.00676 -0.1423 0.4341 0.6745
7.250 1.3766 0.01299 0.00705 -0.1407 0.4231 0.6781
7.500 1.3951 0.01328 0.00735 -0.1391 0.4108 0.6821
7.750 1.4140 0.01359 0.00768 -0.1377 0.3987 0.6865
8.000 1.4316 0.01393 0.00803 -0.1360 0.3856 0.6907
8.250 1.4478 0.01433 0.00843 -0.1341 0.3706 0.6951
8.500 1.4616 0.01484 0.00889 -0.1319 0.3524 0.7003
9.000 1.4876 0.01598 0.00997 -0.1273 0.3151 0.7114
9.250 1.5011 0.01658 0.01055 -0.1252 0.2984 0.7181
9.500 1.5127 0.01727 0.01122 -0.1229 0.2801 0.7244
9.750 1.5226 0.01807 0.01198 -0.1204 0.2611 0.7320
10.000 1.5316 0.01895 0.01283 -0.1178 0.2436 0.7399
10.250 1.5406 0.01986 0.01373 -0.1154 0.2255 0.7495
10.500 1.5479 0.02089 0.01474 -0.1129 0.2069 0.7599
10.750 1.5520 0.02216 0.01596 -0.1100 0.1870 0.7727
11.000 1.5561 0.02348 0.01726 -0.1074 0.1685 0.7888
11.250 1.5598 0.02487 0.01866 -0.1048 0.1513 0.8109
11.500 1.5630 0.02623 0.02009 -0.1022 0.1374 0.8475
11.750 1.5614 0.02751 0.02149 -0.0988 0.1250 1.0000
12.000 1.5641 0.02934 0.02326 -0.0969 0.1107 1.0000
12.250 1.5667 0.03124 0.02512 -0.0950 0.0984 1.0000
12.500 1.5687 0.03327 0.02712 -0.0934 0.0872 1.0000
12.750 1.5699 0.03546 0.02929 -0.0918 0.0769 1.0000
13.000 1.5701 0.03783 0.03163 -0.0903 0.0669 1.0000
13.250 1.5696 0.04038 0.03416 -0.0890 0.0569 1.0000
13.750 1.5624 0.04640 0.04012 -0.0867 0.0360 1.0000
14.000 1.5542 0.05013 0.04381 -0.0858 0.0256 1.0000
14.250 1.5464 0.05395 0.04763 -0.0851 0.0185 1.0000
14.500 1.5411 0.05765 0.05137 -0.0847 0.0149 1.0000
14.750 1.5394 0.06104 0.05484 -0.0845 0.0132 1.0000
15.000 1.5359 0.06476 0.05863 -0.0845 0.0120 1.0000
15.250 1.5337 0.06840 0.06237 -0.0846 0.0113 1.0000
15.500 1.5324 0.07200 0.06608 -0.0849 0.0108 1.0000
15.750 1.5302 0.07582 0.07000 -0.0853 0.0104 1.0000
16.000 1.5271 0.07986 0.07414 -0.0859 0.0101 1.0000
16.250 1.5222 0.08422 0.07860 -0.0867 0.0097 1.0000
16.500 1.5160 0.08889 0.08338 -0.0877 0.0095 1.0000
16.750 1.5083 0.09391 0.08851 -0.0889 0.0092 1.0000
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