EPPLER 547 AIRFOIL (e547-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 547 AIRFOIL (e547-il) Reynolds number: 50,000 Max Cl/Cd: 14.98 at α=13.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e547-il-50000-n5.txt Download as CSV file: xf-e547-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 547 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4179 0.11028 0.10315 -0.0541 1.0000 0.0398
-12.250 -0.4758 0.09310 0.08586 -0.0653 1.0000 0.0354
-12.000 -0.4871 0.08842 0.08118 -0.0669 1.0000 0.0351
-11.750 -0.5050 0.08350 0.07622 -0.0684 1.0000 0.0348
-11.500 -0.5280 0.07876 0.07140 -0.0692 1.0000 0.0348
-11.250 -0.5445 0.07505 0.06764 -0.0689 1.0000 0.0345
-11.000 -0.5648 0.07154 0.06403 -0.0679 1.0000 0.0344
-10.750 -0.5851 0.06849 0.06088 -0.0661 1.0000 0.0344
-10.500 -0.6046 0.06588 0.05817 -0.0634 1.0000 0.0343
-10.250 -0.6256 0.06370 0.05589 -0.0598 1.0000 0.0344
-10.000 -0.6492 0.06206 0.05417 -0.0549 1.0000 0.0345
-9.750 -0.6699 0.06077 0.05283 -0.0496 1.0000 0.0344
-9.500 -0.6898 0.05944 0.05140 -0.0443 1.0000 0.0345
-9.250 -0.7087 0.05814 0.04997 -0.0390 1.0000 0.0346
-9.000 -0.7251 0.05672 0.04837 -0.0339 1.0000 0.0348
-8.750 -0.7077 0.05300 0.04414 -0.0353 0.9895 0.0357
-8.500 -0.6826 0.05008 0.04101 -0.0371 0.9808 0.0371
-8.250 -0.6544 0.04727 0.03787 -0.0386 0.9722 0.0382
-8.000 -0.6223 0.04463 0.03488 -0.0400 0.9643 0.0400
-7.750 -0.5813 0.04227 0.03199 -0.0420 0.9585 0.0439
-7.500 -0.5366 0.04038 0.03011 -0.0447 0.9535 0.0487
-7.250 -0.4712 0.03870 0.02829 -0.0486 0.9524 0.0574
-7.000 -0.4256 0.03742 0.02696 -0.0505 0.9469 0.0698
-6.750 -0.3925 0.03611 0.02567 -0.0518 0.9395 0.0868
-6.500 -0.3698 0.03460 0.02433 -0.0522 0.9298 0.1126
-6.250 -0.3577 0.03287 0.02299 -0.0515 0.9187 0.1563
-6.000 -0.3572 0.03082 0.02164 -0.0497 0.9068 0.2369
-5.500 -0.3106 0.03427 0.02664 -0.0404 0.8882 0.6286
-5.000 -0.2382 0.03772 0.02938 -0.0377 0.8721 0.7020
-4.750 -0.1817 0.03897 0.03022 -0.0397 0.8673 0.7307
-4.500 -0.1307 0.03922 0.03011 -0.0426 0.8610 0.7471
-4.250 -0.0918 0.03897 0.02956 -0.0445 0.8527 0.7569
-4.000 -0.0621 0.03862 0.02897 -0.0452 0.8441 0.7652
-3.750 -0.0375 0.03826 0.02839 -0.0452 0.8353 0.7737
-3.500 -0.0125 0.03797 0.02790 -0.0452 0.8257 0.7802
-3.250 0.0183 0.03753 0.02724 -0.0462 0.8185 0.7862
-3.000 0.0257 0.03739 0.02699 -0.0434 0.8077 0.7933
-2.750 0.0639 0.03688 0.02625 -0.0457 0.8017 0.7974
-2.500 0.0740 0.03681 0.02609 -0.0434 0.7912 0.8033
-2.250 0.0899 0.03653 0.02567 -0.0420 0.7836 0.8085
-2.000 0.1151 0.03634 0.02536 -0.0421 0.7751 0.8122
-1.750 0.1378 0.03606 0.02495 -0.0418 0.7683 0.8164
-1.500 0.1317 0.03612 0.02497 -0.0367 0.7587 0.8226
-1.250 0.1636 0.03581 0.02454 -0.0380 0.7527 0.8250
-1.000 0.1806 0.03580 0.02447 -0.0369 0.7442 0.8286
-0.750 0.2049 0.03548 0.02403 -0.0367 0.7390 0.8319
-0.500 0.1850 0.03581 0.02438 -0.0294 0.7288 0.8377
-0.250 0.2187 0.03549 0.02395 -0.0309 0.7241 0.8397
0.000 0.2261 0.03574 0.02419 -0.0283 0.7151 0.8428
0.250 0.2480 0.03555 0.02393 -0.0277 0.7097 0.8456
0.500 0.2411 0.03583 0.02422 -0.0227 0.7013 0.8501
0.750 0.2484 0.03576 0.02411 -0.0199 0.6952 0.8534
1.000 0.2662 0.03586 0.02418 -0.0189 0.6888 0.8557
1.250 0.2769 0.03606 0.02437 -0.0168 0.6816 0.8588
1.500 0.3024 0.03585 0.02412 -0.0168 0.6775 0.8611
1.750 0.2803 0.03645 0.02475 -0.0097 0.6679 0.8658
2.000 0.2986 0.03632 0.02460 -0.0086 0.6632 0.8687
2.250 0.3014 0.03687 0.02519 -0.0057 0.6552 0.8718
2.500 0.3171 0.03699 0.02531 -0.0044 0.6495 0.8743
2.750 0.3467 0.03676 0.02506 -0.0049 0.6461 0.8763
3.000 0.3155 0.03769 0.02603 0.0029 0.6355 0.8824
3.250 0.3456 0.03759 0.02594 0.0022 0.6318 0.8845
3.500 0.3335 0.03857 0.02698 0.0069 0.6221 0.8888
3.750 0.3579 0.03859 0.02702 0.0069 0.6176 0.8913
4.250 0.3634 0.03974 0.02824 0.0124 0.6033 0.8997
4.500 0.4007 0.03956 0.02811 0.0108 0.6002 0.9018
4.750 0.3838 0.04117 0.02979 0.0150 0.5889 0.9078
5.000 0.4157 0.04095 0.02961 0.0143 0.5855 0.9107
5.500 0.4403 0.04256 0.03138 0.0159 0.5707 0.9187
6.000 0.4683 0.04420 0.03321 0.0169 0.5556 0.9287
6.500 0.5065 0.04585 0.03509 0.0162 0.5404 0.9385
7.000 0.5498 0.04736 0.03686 0.0149 0.5250 0.9486
7.500 0.5981 0.04876 0.03856 0.0128 0.5092 0.9604
8.000 0.6526 0.04980 0.03993 0.0102 0.4931 0.9760
8.250 0.6588 0.05178 0.04207 0.0095 0.4801 0.9972
8.750 0.6857 0.05271 0.04318 0.0113 0.4634 1.0000
9.000 0.6853 0.05471 0.04526 0.0118 0.4508 1.0000
9.250 0.7259 0.05317 0.04390 0.0118 0.4468 1.0000
9.750 0.7311 0.05726 0.04817 0.0121 0.4203 1.0000
10.250 0.7785 0.05715 0.04834 0.0125 0.4025 1.0000
10.500 0.7842 0.05895 0.05027 0.0126 0.3890 1.0000
11.000 0.8045 0.06165 0.05321 0.0128 0.3635 1.0000
11.250 0.8494 0.05879 0.05055 0.0137 0.3569 1.0000
11.750 0.8694 0.06123 0.05325 0.0142 0.3292 1.0000
12.000 0.8832 0.06198 0.05413 0.0146 0.3154 1.0000
12.250 0.8994 0.06242 0.05467 0.0151 0.3012 1.0000
12.500 0.9166 0.06272 0.05506 0.0156 0.2866 1.0000
12.750 0.9336 0.06302 0.05544 0.0162 0.2712 1.0000
13.000 0.9496 0.06344 0.05588 0.0168 0.2551 1.0000
13.250 0.9627 0.06426 0.05667 0.0174 0.2388 1.0000
13.500 0.9689 0.06605 0.05842 0.0176 0.2231 1.0000
13.750 0.9719 0.06833 0.06071 0.0176 0.2081 1.0000
14.000 0.9745 0.07074 0.06310 0.0175 0.1938 1.0000
14.250 0.9768 0.07325 0.06559 0.0173 0.1801 1.0000
14.500 0.9745 0.07659 0.06904 0.0167 0.1679 1.0000
14.750 0.9725 0.08000 0.07250 0.0160 0.1564 1.0000
15.000 0.9719 0.08325 0.07578 0.0153 0.1456 1.0000
15.250 0.9741 0.08605 0.07856 0.0147 0.1356 1.0000
15.500 0.9731 0.08948 0.08203 0.0138 0.1261 1.0000
15.750 0.9688 0.09370 0.08638 0.0125 0.1182 1.0000
16.000 0.9732 0.09625 0.08884 0.0118 0.1100 1.0000
16.250 0.9638 0.10159 0.09442 0.0098 0.1037 1.0000
16.500 0.9697 0.10401 0.09677 0.0091 0.0969 1.0000
16.750 0.9564 0.11033 0.10337 0.0064 0.0924 1.0000
17.000 0.9628 0.11268 0.10566 0.0056 0.0862 1.0000
17.250 0.9497 0.11924 0.11244 0.0025 0.0828 1.0000
17.500 0.9274 0.12801 0.12146 -0.0020 0.0805 1.0000
17.750 0.8960 0.13942 0.13305 -0.0081 0.0792 1.0000
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Polar data table (+)
Polar graphs
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