EPPLER 545 AIRFOIL (e545-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 545 AIRFOIL (e545-il) Reynolds number: 500,000 Max Cl/Cd: 81.84 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e545-il-500000-n5.txt Download as CSV file: xf-e545-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 545 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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.6256 0.09349 0.09071 -0.0569 1.0000 0.0039
-15.000 -0.6670 0.08041 0.07736 -0.0644 1.0000 0.0039
-14.750 -0.6864 0.07327 0.07007 -0.0681 1.0000 0.0038
-14.500 -0.7089 0.06648 0.06308 -0.0710 1.0000 0.0038
-14.250 -0.7282 0.06087 0.05727 -0.0727 1.0000 0.0038
-14.000 -0.7410 0.05657 0.05280 -0.0735 1.0000 0.0038
-13.750 -0.7548 0.05247 0.04852 -0.0737 1.0000 0.0038
-13.500 -0.7641 0.04917 0.04505 -0.0735 1.0000 0.0037
-13.250 -0.7736 0.04598 0.04168 -0.0727 1.0000 0.0037
-13.000 -0.7794 0.04330 0.03882 -0.0718 1.0000 0.0037
-12.750 -0.7829 0.04094 0.03632 -0.0706 1.0000 0.0037
-12.500 -0.7844 0.03886 0.03409 -0.0692 1.0000 0.0037
-12.250 -0.7847 0.03697 0.03207 -0.0676 1.0000 0.0037
-12.000 -0.7840 0.03527 0.03024 -0.0658 1.0000 0.0038
-11.500 -0.7460 0.03136 0.02602 -0.0688 0.9914 0.0038
-11.250 -0.7328 0.02976 0.02430 -0.0686 0.9787 0.0038
-11.000 -0.7137 0.02832 0.02274 -0.0693 0.9626 0.0039
-10.750 -0.6850 0.02677 0.02106 -0.0720 0.9514 0.0039
-10.500 -0.6497 0.02525 0.01940 -0.0759 0.9415 0.0040
-10.250 -0.6060 0.02382 0.01785 -0.0815 0.9323 0.0041
-10.000 -0.5603 0.02242 0.01631 -0.0874 0.9208 0.0042
-9.750 -0.5186 0.02128 0.01502 -0.0923 0.9034 0.0043
-9.500 -0.4895 0.02040 0.01399 -0.0944 0.8824 0.0044
-9.250 -0.4710 0.01964 0.01309 -0.0942 0.8620 0.0046
-9.000 -0.4588 0.01883 0.01215 -0.0928 0.8447 0.0049
-8.750 -0.4441 0.01828 0.01150 -0.0915 0.8296 0.0049
-8.500 -0.4308 0.01770 0.01083 -0.0900 0.8161 0.0051
-8.250 -0.4171 0.01716 0.01020 -0.0884 0.8046 0.0052
-8.000 -0.4048 0.01659 0.00953 -0.0866 0.7936 0.0058
-7.750 -0.3924 0.01604 0.00890 -0.0847 0.7826 0.0062
-7.500 -0.3817 0.01549 0.00828 -0.0826 0.7729 0.0068
-7.250 -0.3722 0.01500 0.00773 -0.0801 0.7626 0.0074
-7.000 -0.3633 0.01462 0.00728 -0.0773 0.7541 0.0086
-6.750 -0.3487 0.01424 0.00685 -0.0755 0.7458 0.0103
-6.500 -0.3325 0.01389 0.00644 -0.0739 0.7384 0.0133
-6.250 -0.3149 0.01351 0.00607 -0.0725 0.7309 0.0183
-6.000 -0.2963 0.01319 0.00572 -0.0713 0.7233 0.0249
-5.750 -0.2779 0.01279 0.00536 -0.0701 0.7163 0.0390
-5.500 -0.2604 0.01230 0.00499 -0.0689 0.7087 0.0661
-5.250 -0.2437 0.01171 0.00458 -0.0675 0.7019 0.1117
-5.000 -0.2265 0.01102 0.00416 -0.0664 0.6944 0.1754
-4.750 -0.2111 0.01009 0.00361 -0.0652 0.6874 0.2766
-4.500 -0.1980 0.00872 0.00288 -0.0638 0.6806 0.4412
-4.250 -0.1748 0.00837 0.00284 -0.0633 0.6735 0.5400
-4.000 -0.1476 0.00841 0.00284 -0.0633 0.6667 0.5616
-3.750 -0.1194 0.00847 0.00285 -0.0634 0.6611 0.5776
-3.500 -0.0913 0.00858 0.00289 -0.0635 0.6550 0.5922
-3.250 -0.0635 0.00876 0.00302 -0.0634 0.6490 0.6042
-3.000 -0.0355 0.00890 0.00313 -0.0634 0.6427 0.6132
-2.750 -0.0075 0.00898 0.00316 -0.0635 0.6362 0.6177
-2.500 0.0205 0.00899 0.00308 -0.0637 0.6307 0.6192
-2.250 0.0490 0.00897 0.00299 -0.0640 0.6259 0.6204
-2.000 0.0774 0.00897 0.00292 -0.0643 0.6208 0.6218
-1.750 0.1056 0.00898 0.00286 -0.0645 0.6156 0.6232
-1.500 0.1337 0.00899 0.00279 -0.0647 0.6107 0.6243
-1.250 0.1622 0.00899 0.00274 -0.0650 0.6057 0.6253
-1.000 0.1904 0.00898 0.00269 -0.0653 0.6008 0.6263
-0.750 0.2183 0.00899 0.00265 -0.0654 0.5962 0.6273
-0.500 0.2464 0.00900 0.00264 -0.0656 0.5916 0.6283
-0.250 0.2746 0.00900 0.00263 -0.0659 0.5867 0.6295
0.000 0.3027 0.00903 0.00263 -0.0661 0.5820 0.6308
0.250 0.3304 0.00907 0.00264 -0.0662 0.5775 0.6319
0.500 0.3585 0.00909 0.00265 -0.0664 0.5731 0.6330
0.750 0.3866 0.00912 0.00267 -0.0666 0.5683 0.6341
1.000 0.4143 0.00916 0.00268 -0.0668 0.5628 0.6353
1.250 0.4417 0.00921 0.00270 -0.0669 0.5577 0.6365
1.500 0.4698 0.00924 0.00274 -0.0671 0.5528 0.6377
1.750 0.4975 0.00928 0.00277 -0.0672 0.5475 0.6389
2.000 0.5246 0.00935 0.00281 -0.0673 0.5420 0.6401
2.250 0.5522 0.00940 0.00285 -0.0674 0.5360 0.6413
2.500 0.5792 0.00946 0.00290 -0.0675 0.5284 0.6425
2.750 0.6057 0.00954 0.00296 -0.0674 0.5204 0.6437
3.000 0.6323 0.00960 0.00302 -0.0673 0.5114 0.6451
3.250 0.6584 0.00968 0.00310 -0.0672 0.5038 0.6465
3.500 0.6851 0.00974 0.00319 -0.0671 0.4957 0.6477
3.750 0.7107 0.00984 0.00329 -0.0669 0.4878 0.6490
4.000 0.7374 0.00991 0.00339 -0.0669 0.4800 0.6503
4.250 0.7627 0.01003 0.00351 -0.0666 0.4714 0.6516
4.500 0.7889 0.01012 0.00362 -0.0665 0.4628 0.6530
4.750 0.8135 0.01026 0.00375 -0.0661 0.4519 0.6545
5.000 0.8374 0.01042 0.00390 -0.0655 0.4378 0.6560
5.250 0.8612 0.01059 0.00406 -0.0650 0.4235 0.6575
5.500 0.8839 0.01080 0.00424 -0.0642 0.4077 0.6590
5.750 0.9052 0.01106 0.00444 -0.0633 0.3892 0.6604
6.000 0.9248 0.01138 0.00469 -0.0620 0.3673 0.6618
6.250 0.9405 0.01182 0.00501 -0.0600 0.3369 0.6634
6.500 0.9533 0.01234 0.00541 -0.0576 0.3036 0.6652
6.750 0.9640 0.01284 0.00580 -0.0547 0.2742 0.6670
7.000 0.9757 0.01331 0.00619 -0.0521 0.2516 0.6689
7.250 0.9894 0.01376 0.00659 -0.0499 0.2341 0.6708
7.500 1.0034 0.01422 0.00702 -0.0478 0.2209 0.6726
7.750 1.0188 0.01463 0.00743 -0.0459 0.2123 0.6746
8.000 1.0333 0.01508 0.00788 -0.0440 0.2043 0.6765
8.250 1.0484 0.01552 0.00833 -0.0422 0.1973 0.6784
8.500 1.0616 0.01603 0.00885 -0.0402 0.1905 0.6802
8.750 1.0780 0.01642 0.00930 -0.0388 0.1828 0.6822
9.000 1.0915 0.01694 0.00985 -0.0369 0.1720 0.6843
9.250 1.0967 0.01785 0.01061 -0.0341 0.1348 0.6865
9.500 1.1019 0.01882 0.01150 -0.0314 0.1205 0.6888
9.750 1.1100 0.01970 0.01240 -0.0293 0.1131 0.6913
10.000 1.1202 0.02053 0.01327 -0.0275 0.1057 0.6940
10.250 1.1300 0.02142 0.01419 -0.0257 0.0984 0.6968
10.750 1.1464 0.02350 0.01629 -0.0222 0.0800 0.7022
11.000 1.1530 0.02470 0.01748 -0.0205 0.0703 0.7052
11.250 1.1599 0.02593 0.01873 -0.0190 0.0626 0.7083
11.500 1.1666 0.02724 0.02006 -0.0176 0.0556 0.7116
11.750 1.1732 0.02861 0.02144 -0.0162 0.0496 0.7148
12.250 1.1855 0.03154 0.02443 -0.0138 0.0386 0.7214
12.500 1.1913 0.03309 0.02602 -0.0127 0.0341 0.7254
12.750 1.1974 0.03468 0.02766 -0.0118 0.0308 0.7295
13.000 1.2025 0.03641 0.02942 -0.0109 0.0271 0.7337
13.250 1.2079 0.03815 0.03122 -0.0102 0.0242 0.7379
13.500 1.2139 0.03989 0.03304 -0.0095 0.0219 0.7430
13.750 1.2188 0.04178 0.03500 -0.0089 0.0195 0.7484
14.250 1.2291 0.04568 0.03906 -0.0080 0.0163 0.7608
14.500 1.2331 0.04782 0.04129 -0.0077 0.0150 0.7683
14.750 1.2378 0.04996 0.04352 -0.0075 0.0136 0.7763
15.000 1.2413 0.05225 0.04592 -0.0074 0.0125 0.7859
15.250 1.2448 0.05459 0.04837 -0.0073 0.0114 0.7964
15.500 1.2472 0.05710 0.05098 -0.0074 0.0103 0.8090
15.750 1.2501 0.05955 0.05357 -0.0074 0.0093 0.8261
16.000 1.2502 0.06221 0.05640 -0.0073 0.0086 0.8533
16.250 1.2572 0.06497 0.05944 -0.0089 0.0078 0.9885
16.750 1.2569 0.07113 0.06575 -0.0098 0.0067 1.0000
17.000 1.2577 0.07434 0.06905 -0.0106 0.0061 1.0000
17.250 1.2574 0.07775 0.07255 -0.0116 0.0057 1.0000
17.500 1.2554 0.08148 0.07636 -0.0127 0.0052 1.0000
17.750 1.2533 0.08529 0.08027 -0.0140 0.0050 1.0000
18.000 1.2515 0.08917 0.08425 -0.0153 0.0048 1.0000
18.250 1.2486 0.09328 0.08847 -0.0169 0.0045 1.0000
18.500 1.2452 0.09755 0.09283 -0.0186 0.0042 1.0000
18.750 1.2403 0.10212 0.09751 -0.0205 0.0040 1.0000
19.000 1.2347 0.10690 0.10239 -0.0227 0.0039 1.0000
19.250 1.2283 0.11189 0.10748 -0.0250 0.0037 1.0000
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Polar data table (+)
Polar graphs
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