EPPLER 580 AIRFOIL (e580-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 580 AIRFOIL (e580-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.73 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e580-il-1000000-n5.txt Download as CSV file: xf-e580-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5620 0.07059 0.06829 -0.0943 0.9915 0.0081
-14.000 -0.5768 0.06254 0.06006 -0.1010 0.9900 0.0082
-13.750 -0.5962 0.05463 0.05195 -0.1078 0.9883 0.0082
-13.500 -0.6082 0.04846 0.04559 -0.1135 0.9867 0.0082
-13.250 -0.6044 0.04461 0.04160 -0.1177 0.9854 0.0082
-13.000 -0.6029 0.04039 0.03720 -0.1224 0.9842 0.0083
-12.750 -0.6005 0.03784 0.03454 -0.1237 0.9811 0.0083
-12.500 -0.5975 0.03512 0.03169 -0.1255 0.9774 0.0083
-12.250 -0.5865 0.03260 0.02903 -0.1283 0.9749 0.0084
-12.000 -0.5750 0.02976 0.02601 -0.1314 0.9729 0.0084
-11.750 -0.5743 0.02753 0.02364 -0.1312 0.9670 0.0085
-11.500 -0.5629 0.02562 0.02162 -0.1323 0.9622 0.0086
-11.000 -0.5435 0.02273 0.01853 -0.1318 0.9480 0.0087
-10.750 -0.5292 0.02157 0.01731 -0.1319 0.9395 0.0089
-10.500 -0.4995 0.02042 0.01607 -0.1348 0.9338 0.0090
-10.250 -0.4672 0.01925 0.01481 -0.1380 0.9278 0.0091
-10.000 -0.4315 0.01825 0.01370 -0.1414 0.9203 0.0092
-9.750 -0.3979 0.01737 0.01273 -0.1442 0.9107 0.0093
-9.500 -0.3668 0.01660 0.01185 -0.1461 0.8988 0.0095
-9.250 -0.3404 0.01591 0.01103 -0.1470 0.8844 0.0096
-9.000 -0.3166 0.01537 0.01037 -0.1472 0.8692 0.0097
-8.750 -0.2945 0.01486 0.00974 -0.1470 0.8549 0.0099
-8.500 -0.2724 0.01440 0.00918 -0.1466 0.8415 0.0101
-8.000 -0.2271 0.01358 0.00818 -0.1459 0.8158 0.0105
-7.750 -0.2039 0.01319 0.00769 -0.1456 0.8037 0.0107
-7.500 -0.1803 0.01280 0.00721 -0.1454 0.7927 0.0109
-7.250 -0.1564 0.01245 0.00677 -0.1451 0.7812 0.0111
-7.000 -0.1315 0.01211 0.00637 -0.1451 0.7701 0.0112
-6.750 -0.1060 0.01185 0.00602 -0.1450 0.7601 0.0113
-6.500 -0.0808 0.01151 0.00561 -0.1450 0.7499 0.0115
-6.250 -0.0549 0.01103 0.00505 -0.1452 0.7401 0.0119
-6.000 -0.0285 0.01072 0.00468 -0.1454 0.7305 0.0122
-5.750 -0.0017 0.01047 0.00437 -0.1455 0.7209 0.0124
-5.500 0.0257 0.01024 0.00409 -0.1458 0.7123 0.0128
-5.250 0.0528 0.01006 0.00384 -0.1459 0.7032 0.0131
-5.000 0.0807 0.00987 0.00361 -0.1462 0.6944 0.0135
-4.750 0.1083 0.00971 0.00339 -0.1464 0.6861 0.0139
-4.500 0.1364 0.00956 0.00320 -0.1466 0.6775 0.0145
-4.250 0.1642 0.00946 0.00304 -0.1468 0.6693 0.0149
-4.000 0.1924 0.00931 0.00284 -0.1471 0.6611 0.0158
-3.750 0.2206 0.00919 0.00267 -0.1474 0.6532 0.0168
-3.500 0.2488 0.00910 0.00254 -0.1476 0.6451 0.0178
-3.250 0.2770 0.00902 0.00242 -0.1479 0.6378 0.0193
-3.000 0.3056 0.00890 0.00230 -0.1482 0.6301 0.0268
-2.750 0.3351 0.00858 0.00214 -0.1490 0.6231 0.0854
-2.500 0.3654 0.00819 0.00198 -0.1501 0.6159 0.1667
-2.250 0.3988 0.00720 0.00165 -0.1526 0.6092 0.3968
-2.000 0.4287 0.00700 0.00167 -0.1534 0.6024 0.4787
-1.750 0.4569 0.00705 0.00173 -0.1535 0.5956 0.5079
-1.500 0.4854 0.00710 0.00176 -0.1537 0.5895 0.5179
-1.250 0.5135 0.00716 0.00179 -0.1538 0.5828 0.5249
-1.000 0.5415 0.00724 0.00181 -0.1538 0.5767 0.5304
-0.750 0.5698 0.00728 0.00184 -0.1540 0.5704 0.5333
-0.500 0.5974 0.00736 0.00186 -0.1540 0.5641 0.5353
-0.250 0.6257 0.00740 0.00189 -0.1542 0.5584 0.5374
0.000 0.6536 0.00747 0.00192 -0.1542 0.5520 0.5395
0.250 0.6812 0.00755 0.00196 -0.1542 0.5461 0.5413
0.500 0.7092 0.00761 0.00199 -0.1543 0.5401 0.5431
0.750 0.7366 0.00770 0.00204 -0.1543 0.5337 0.5448
1.000 0.7644 0.00776 0.00209 -0.1544 0.5280 0.5467
1.250 0.7919 0.00783 0.00214 -0.1544 0.5213 0.5486
1.500 0.8191 0.00792 0.00221 -0.1544 0.5150 0.5503
1.750 0.8466 0.00799 0.00228 -0.1544 0.5086 0.5522
2.250 0.9007 0.00818 0.00243 -0.1543 0.4949 0.5564
2.500 0.9272 0.00830 0.00252 -0.1541 0.4874 0.5582
2.750 0.9541 0.00840 0.00260 -0.1540 0.4801 0.5599
3.250 1.0068 0.00863 0.00280 -0.1536 0.4640 0.5634
3.750 1.0586 0.00890 0.00304 -0.1531 0.4461 0.5676
4.000 1.0838 0.00905 0.00318 -0.1527 0.4367 0.5697
4.250 1.1087 0.00923 0.00332 -0.1523 0.4259 0.5716
4.500 1.1335 0.00940 0.00347 -0.1518 0.4147 0.5736
4.750 1.1578 0.00959 0.00363 -0.1513 0.4038 0.5755
5.000 1.1815 0.00981 0.00381 -0.1506 0.3926 0.5773
5.250 1.2049 0.01001 0.00399 -0.1499 0.3807 0.5797
5.500 1.2276 0.01022 0.00418 -0.1491 0.3690 0.5819
5.750 1.2495 0.01044 0.00439 -0.1481 0.3576 0.5841
6.000 1.2705 0.01071 0.00461 -0.1469 0.3445 0.5863
6.250 1.2912 0.01099 0.00485 -0.1457 0.3319 0.5886
6.500 1.3119 0.01128 0.00511 -0.1446 0.3192 0.5908
6.750 1.3318 0.01161 0.00540 -0.1433 0.3047 0.5929
7.000 1.3510 0.01197 0.00571 -0.1418 0.2895 0.5955
7.250 1.3685 0.01240 0.00608 -0.1402 0.2714 0.5983
7.500 1.3841 0.01293 0.00651 -0.1382 0.2481 0.6010
7.750 1.3983 0.01353 0.00700 -0.1360 0.2247 0.6037
8.000 1.4114 0.01416 0.00752 -0.1337 0.2022 0.6063
8.250 1.4238 0.01485 0.00809 -0.1313 0.1795 0.6087
8.500 1.4346 0.01560 0.00874 -0.1287 0.1580 0.6114
8.750 1.4475 0.01627 0.00935 -0.1265 0.1420 0.6144
9.000 1.4597 0.01698 0.01001 -0.1242 0.1272 0.6176
9.250 1.4700 0.01779 0.01076 -0.1218 0.1104 0.6210
9.500 1.4798 0.01866 0.01156 -0.1193 0.0960 0.6244
9.750 1.4895 0.01955 0.01241 -0.1169 0.0833 0.6280
10.000 1.5000 0.02043 0.01327 -0.1147 0.0732 0.6320
10.250 1.5083 0.02147 0.01428 -0.1124 0.0621 0.6360
10.500 1.5169 0.02252 0.01532 -0.1102 0.0535 0.6399
10.750 1.5233 0.02376 0.01654 -0.1078 0.0435 0.6438
11.000 1.5308 0.02499 0.01776 -0.1057 0.0366 0.6484
11.250 1.5368 0.02637 0.01914 -0.1036 0.0295 0.6532
11.750 1.5470 0.02946 0.02225 -0.0996 0.0174 0.6631
12.000 1.5468 0.03153 0.02433 -0.0974 0.0096 0.6690
12.250 1.5507 0.03338 0.02622 -0.0958 0.0068 0.6751
12.500 1.5576 0.03504 0.02795 -0.0945 0.0059 0.6825
12.750 1.5640 0.03680 0.02978 -0.0933 0.0053 0.6898
13.000 1.5706 0.03861 0.03167 -0.0923 0.0049 0.6983
13.250 1.5777 0.04043 0.03358 -0.0913 0.0047 0.7067
13.500 1.5842 0.04236 0.03561 -0.0905 0.0045 0.7167
13.750 1.5899 0.04443 0.03777 -0.0898 0.0043 0.7273
14.000 1.5951 0.04662 0.04007 -0.0891 0.0042 0.7396
14.250 1.5997 0.04893 0.04248 -0.0885 0.0041 0.7541
14.500 1.6037 0.05139 0.04505 -0.0881 0.0039 0.7719
14.750 1.6069 0.05398 0.04778 -0.0877 0.0038 0.7957
15.000 1.6091 0.05670 0.05067 -0.0874 0.0037 0.8357
15.250 1.6069 0.05928 0.05353 -0.0863 0.0036 1.0000
15.500 1.6072 0.06247 0.05680 -0.0863 0.0034 1.0000
15.750 1.6074 0.06573 0.06015 -0.0864 0.0034 1.0000
16.000 1.6086 0.06891 0.06340 -0.0865 0.0033 1.0000
16.250 1.6091 0.07226 0.06685 -0.0869 0.0033 1.0000
16.500 1.6090 0.07576 0.07044 -0.0873 0.0032 1.0000
16.750 1.6086 0.07937 0.07414 -0.0878 0.0032 1.0000
17.000 1.6074 0.08315 0.07800 -0.0885 0.0032 1.0000
17.250 1.6057 0.08707 0.08201 -0.0893 0.0031 1.0000
17.500 1.6034 0.09113 0.08617 -0.0902 0.0031 1.0000
17.750 1.6007 0.09533 0.09046 -0.0913 0.0030 1.0000
18.000 1.5971 0.09974 0.09496 -0.0925 0.0030 1.0000
18.250 1.5932 0.10422 0.09954 -0.0939 0.0029 1.0000
18.500 1.5890 0.10880 0.10421 -0.0954 0.0029 1.0000
18.750 1.5846 0.11346 0.10897 -0.0971 0.0029 1.0000
19.000 1.5799 0.11822 0.11382 -0.0988 0.0028 1.0000
19.250 1.5749 0.12304 0.11874 -0.1008 0.0028 1.0000
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Polar data table (+)
Polar graphs
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