EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: EPPLER 580 AIRFOIL (e580-il) Reynolds number: 500,000 Max Cl/Cd: 101.96 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e580-il-500000-n5.txt Download as CSV file: xf-e580-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4216 0.07156 0.06892 -0.0908 0.9875 0.0110
-12.000 -0.4471 0.06042 0.05756 -0.1015 0.9852 0.0108
-11.750 -0.4686 0.05226 0.04915 -0.1093 0.9819 0.0109
-11.500 -0.4835 0.04642 0.04307 -0.1142 0.9763 0.0109
-11.000 -0.4935 0.03790 0.03409 -0.1213 0.9646 0.0109
-10.750 -0.4883 0.03437 0.03028 -0.1249 0.9596 0.0111
-10.500 -0.4912 0.03240 0.02814 -0.1241 0.9486 0.0112
-10.250 -0.4882 0.03018 0.02570 -0.1242 0.9382 0.0112
-10.000 -0.4697 0.02810 0.02338 -0.1263 0.9327 0.0113
-9.750 -0.4554 0.02662 0.02170 -0.1263 0.9236 0.0114
-9.250 -0.4070 0.02269 0.01739 -0.1294 0.9126 0.0117
-9.000 -0.3751 0.02136 0.01595 -0.1317 0.9075 0.0119
-8.750 -0.3375 0.02022 0.01471 -0.1350 0.9035 0.0122
-8.500 -0.3070 0.01934 0.01375 -0.1367 0.8952 0.0125
-8.000 -0.2416 0.01763 0.01181 -0.1405 0.8784 0.0131
-7.750 -0.2121 0.01684 0.01090 -0.1416 0.8684 0.0134
-7.500 -0.1836 0.01614 0.01009 -0.1425 0.8578 0.0137
-7.250 -0.1581 0.01553 0.00938 -0.1426 0.8463 0.0139
-7.000 -0.1328 0.01499 0.00874 -0.1428 0.8348 0.0141
-6.750 -0.1073 0.01449 0.00814 -0.1429 0.8237 0.0145
-6.250 -0.0566 0.01365 0.00711 -0.1430 0.8017 0.0149
-6.000 -0.0314 0.01313 0.00652 -0.1432 0.7911 0.0153
-5.750 -0.0056 0.01264 0.00594 -0.1434 0.7809 0.0157
-5.500 0.0207 0.01225 0.00549 -0.1437 0.7706 0.0161
-5.250 0.0475 0.01195 0.00512 -0.1439 0.7610 0.0168
-5.000 0.0745 0.01170 0.00479 -0.1441 0.7512 0.0177
-4.750 0.1019 0.01146 0.00448 -0.1443 0.7417 0.0185
-4.500 0.1294 0.01126 0.00419 -0.1445 0.7329 0.0191
-4.250 0.1570 0.01104 0.00390 -0.1448 0.7235 0.0200
-4.000 0.1849 0.01085 0.00365 -0.1451 0.7149 0.0216
-3.750 0.2127 0.01071 0.00344 -0.1453 0.7061 0.0237
-3.500 0.2410 0.01049 0.00324 -0.1457 0.6978 0.0342
-3.250 0.2701 0.01002 0.00297 -0.1466 0.6892 0.1035
-3.000 0.3017 0.00914 0.00259 -0.1487 0.6812 0.2599
-2.750 0.3332 0.00840 0.00238 -0.1506 0.6731 0.4404
-2.500 0.3619 0.00840 0.00247 -0.1508 0.6652 0.4948
-2.000 0.4178 0.00864 0.00266 -0.1508 0.6498 0.5357
-1.750 0.4456 0.00878 0.00268 -0.1508 0.6424 0.5452
-1.500 0.4734 0.00882 0.00271 -0.1508 0.6352 0.5491
-1.250 0.5010 0.00888 0.00270 -0.1508 0.6281 0.5511
-1.000 0.5288 0.00894 0.00270 -0.1509 0.6213 0.5533
-0.750 0.5565 0.00900 0.00270 -0.1509 0.6143 0.5557
-0.500 0.5842 0.00907 0.00271 -0.1509 0.6078 0.5580
-0.250 0.6120 0.00913 0.00272 -0.1510 0.6010 0.5600
0.250 0.6669 0.00925 0.00278 -0.1510 0.5881 0.5639
0.500 0.6940 0.00933 0.00283 -0.1509 0.5815 0.5659
0.750 0.7214 0.00941 0.00288 -0.1509 0.5754 0.5678
1.000 0.7487 0.00948 0.00293 -0.1509 0.5688 0.5698
1.250 0.7755 0.00959 0.00299 -0.1508 0.5627 0.5720
1.500 0.8030 0.00966 0.00305 -0.1508 0.5563 0.5743
1.750 0.8297 0.00977 0.00312 -0.1506 0.5498 0.5765
2.000 0.8567 0.00985 0.00320 -0.1506 0.5436 0.5783
2.250 0.8832 0.00994 0.00329 -0.1504 0.5367 0.5801
2.500 0.9095 0.01005 0.00339 -0.1502 0.5304 0.5820
2.750 0.9361 0.01014 0.00350 -0.1501 0.5234 0.5842
3.000 0.9616 0.01028 0.00361 -0.1497 0.5166 0.5866
3.250 0.9882 0.01038 0.00372 -0.1496 0.5093 0.5890
3.500 1.0134 0.01052 0.00385 -0.1492 0.5020 0.5911
3.750 1.0394 0.01064 0.00396 -0.1489 0.4944 0.5931
4.000 1.0640 0.01079 0.00412 -0.1484 0.4865 0.5951
4.250 1.0895 0.01091 0.00427 -0.1481 0.4784 0.5973
4.500 1.1133 0.01109 0.00444 -0.1475 0.4698 0.5998
4.750 1.1380 0.01124 0.00460 -0.1470 0.4605 0.6024
5.000 1.1615 0.01142 0.00479 -0.1463 0.4510 0.6049
5.250 1.1837 0.01164 0.00498 -0.1454 0.4405 0.6073
5.500 1.2062 0.01183 0.00517 -0.1445 0.4296 0.6096
5.750 1.2275 0.01204 0.00539 -0.1433 0.4192 0.6118
6.000 1.2475 0.01229 0.00564 -0.1420 0.4081 0.6144
6.250 1.2680 0.01255 0.00590 -0.1408 0.3961 0.6174
6.500 1.2886 0.01283 0.00617 -0.1396 0.3846 0.6205
6.750 1.3081 0.01315 0.00648 -0.1382 0.3721 0.6235
7.000 1.3270 0.01350 0.00682 -0.1368 0.3597 0.6262
7.250 1.3454 0.01387 0.00718 -0.1353 0.3471 0.6290
7.750 1.3811 0.01468 0.00798 -0.1322 0.3200 0.6354
8.000 1.3981 0.01513 0.00841 -0.1305 0.3062 0.6389
8.250 1.4137 0.01565 0.00891 -0.1287 0.2905 0.6424
8.500 1.4258 0.01633 0.00952 -0.1263 0.2693 0.6462
8.750 1.4359 0.01714 0.01023 -0.1237 0.2452 0.6504
9.000 1.4444 0.01805 0.01104 -0.1210 0.2199 0.6546
9.250 1.4529 0.01900 0.01189 -0.1184 0.1988 0.6586
9.500 1.4628 0.01989 0.01275 -0.1160 0.1810 0.6630
9.750 1.4709 0.02092 0.01372 -0.1136 0.1627 0.6679
10.250 1.4857 0.02317 0.01590 -0.1088 0.1316 0.6779
10.500 1.4934 0.02435 0.01707 -0.1066 0.1189 0.6840
10.750 1.5000 0.02564 0.01835 -0.1045 0.1064 0.6903
11.000 1.5053 0.02708 0.01978 -0.1023 0.0937 0.6974
11.250 1.5082 0.02877 0.02144 -0.1001 0.0801 0.7049
11.500 1.5125 0.03041 0.02309 -0.0982 0.0695 0.7131
11.750 1.5178 0.03206 0.02478 -0.0965 0.0613 0.7219
12.000 1.5215 0.03392 0.02666 -0.0949 0.0530 0.7317
12.250 1.5236 0.03598 0.02875 -0.0933 0.0447 0.7425
12.500 1.5255 0.03815 0.03096 -0.0919 0.0374 0.7549
12.750 1.5281 0.04034 0.03322 -0.0906 0.0315 0.7698
13.000 1.5306 0.04261 0.03557 -0.0895 0.0264 0.7888
13.250 1.5313 0.04510 0.03816 -0.0885 0.0213 0.8150
13.500 1.5306 0.04766 0.04086 -0.0873 0.0165 0.8682
13.750 1.5254 0.05035 0.04367 -0.0857 0.0123 1.0000
14.000 1.5246 0.05340 0.04676 -0.0852 0.0097 1.0000
14.250 1.5252 0.05637 0.04980 -0.0849 0.0084 1.0000
14.500 1.5263 0.05938 0.05288 -0.0847 0.0077 1.0000
14.750 1.5264 0.06258 0.05617 -0.0846 0.0071 1.0000
15.000 1.5269 0.06581 0.05949 -0.0847 0.0066 1.0000
15.250 1.5279 0.06903 0.06281 -0.0848 0.0064 1.0000
15.500 1.5282 0.07241 0.06629 -0.0851 0.0061 1.0000
15.750 1.5280 0.07596 0.06994 -0.0856 0.0059 1.0000
16.000 1.5270 0.07967 0.07375 -0.0861 0.0057 1.0000
16.250 1.5252 0.08356 0.07774 -0.0868 0.0055 1.0000
16.500 1.5228 0.08761 0.08189 -0.0876 0.0053 1.0000
16.750 1.5196 0.09185 0.08624 -0.0886 0.0052 1.0000
17.000 1.5153 0.09635 0.09085 -0.0898 0.0051 1.0000
17.250 1.5104 0.10101 0.09562 -0.0911 0.0050 1.0000
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