EPPLER 547 AIRFOIL (e547-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 547 AIRFOIL (e547-il) Reynolds number: 500,000 Max Cl/Cd: 85.58 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e547-il-500000-n5.txt Download as CSV file: xf-e547-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.6338 0.08762 0.08482 -0.0556 1.0000 0.0041
-14.750 -0.6679 0.07585 0.07282 -0.0629 1.0000 0.0041
-14.500 -0.6970 0.06723 0.06399 -0.0674 1.0000 0.0040
-14.250 -0.7125 0.06186 0.05846 -0.0696 1.0000 0.0040
-14.000 -0.7343 0.05626 0.05265 -0.0709 1.0000 0.0040
-13.750 -0.7466 0.05238 0.04861 -0.0712 1.0000 0.0040
-13.500 -0.7574 0.04894 0.04500 -0.0709 1.0000 0.0040
-13.250 -0.7688 0.04558 0.04145 -0.0701 1.0000 0.0040
-13.000 -0.7773 0.04266 0.03833 -0.0689 1.0000 0.0040
-12.750 -0.7826 0.04015 0.03565 -0.0675 1.0000 0.0040
-12.500 -0.7868 0.03779 0.03311 -0.0657 1.0000 0.0040
-12.250 -0.7879 0.03579 0.03095 -0.0639 1.0000 0.0040
-12.000 -0.7854 0.03424 0.02929 -0.0621 1.0000 0.0040
-11.750 -0.7839 0.03257 0.02747 -0.0600 1.0000 0.0040
-11.500 -0.7681 0.03053 0.02524 -0.0604 0.9914 0.0041
-11.250 -0.7495 0.02898 0.02355 -0.0610 0.9697 0.0041
-11.000 -0.7159 0.02721 0.02159 -0.0646 0.9528 0.0042
-10.750 -0.6730 0.02557 0.01977 -0.0699 0.9417 0.0042
-10.250 -0.5844 0.02250 0.01635 -0.0808 0.9053 0.0044
-10.000 -0.5586 0.02144 0.01512 -0.0822 0.8798 0.0047
-9.750 -0.5406 0.02078 0.01432 -0.0815 0.8580 0.0048
-9.500 -0.5256 0.02012 0.01352 -0.0802 0.8403 0.0047
-9.250 -0.5108 0.01953 0.01281 -0.0788 0.8248 0.0048
-9.000 -0.4956 0.01898 0.01217 -0.0774 0.8114 0.0052
-8.750 -0.4808 0.01841 0.01151 -0.0758 0.7991 0.0054
-8.500 -0.4663 0.01784 0.01084 -0.0742 0.7872 0.0057
-8.250 -0.4509 0.01734 0.01024 -0.0727 0.7761 0.0058
-8.000 -0.4355 0.01684 0.00965 -0.0712 0.7664 0.0062
-7.750 -0.4215 0.01628 0.00903 -0.0694 0.7565 0.0067
-7.500 -0.4060 0.01582 0.00851 -0.0678 0.7474 0.0070
-7.250 -0.3908 0.01540 0.00800 -0.0661 0.7388 0.0075
-7.000 -0.3759 0.01496 0.00750 -0.0643 0.7297 0.0083
-6.750 -0.3623 0.01455 0.00703 -0.0623 0.7216 0.0091
-6.500 -0.3492 0.01421 0.00665 -0.0600 0.7134 0.0107
-6.250 -0.3361 0.01391 0.00630 -0.0576 0.7059 0.0130
-6.000 -0.3197 0.01358 0.00596 -0.0559 0.6978 0.0171
-5.750 -0.3028 0.01325 0.00562 -0.0543 0.6908 0.0244
-5.500 -0.2847 0.01291 0.00531 -0.0529 0.6835 0.0351
-5.000 -0.2489 0.01216 0.00470 -0.0500 0.6702 0.0770
-4.750 -0.2314 0.01173 0.00439 -0.0486 0.6633 0.1131
-4.500 -0.2140 0.01122 0.00407 -0.0472 0.6568 0.1642
-4.250 -0.2001 0.01046 0.00366 -0.0453 0.6501 0.2535
-4.000 -0.1903 0.00932 0.00308 -0.0430 0.6445 0.3981
-3.750 -0.1785 0.00826 0.00275 -0.0407 0.6386 0.5738
-3.500 -0.1522 0.00829 0.00280 -0.0404 0.6325 0.6137
-3.250 -0.1246 0.00837 0.00283 -0.0404 0.6265 0.6346
-3.000 -0.0969 0.00850 0.00289 -0.0404 0.6201 0.6512
-2.750 -0.0694 0.00869 0.00303 -0.0402 0.6147 0.6634
-2.500 -0.0414 0.00888 0.00320 -0.0401 0.6091 0.6735
-2.250 -0.0136 0.00904 0.00328 -0.0401 0.6034 0.6811
-2.000 0.0144 0.00905 0.00319 -0.0403 0.5980 0.6830
-1.750 0.0427 0.00903 0.00312 -0.0406 0.5923 0.6839
-1.500 0.0708 0.00903 0.00305 -0.0408 0.5870 0.6848
-1.250 0.0989 0.00904 0.00301 -0.0410 0.5822 0.6859
-1.000 0.1273 0.00905 0.00298 -0.0412 0.5768 0.6869
-0.750 0.1553 0.00907 0.00294 -0.0414 0.5716 0.6879
-0.500 0.1833 0.00909 0.00291 -0.0416 0.5668 0.6888
-0.250 0.2116 0.00910 0.00289 -0.0419 0.5619 0.6898
0.000 0.2396 0.00912 0.00287 -0.0421 0.5571 0.6909
0.250 0.2674 0.00917 0.00286 -0.0423 0.5526 0.6921
0.500 0.2957 0.00918 0.00286 -0.0426 0.5477 0.6933
0.750 0.3237 0.00922 0.00285 -0.0428 0.5430 0.6944
1.000 0.3514 0.00927 0.00286 -0.0430 0.5386 0.6955
1.250 0.3796 0.00929 0.00287 -0.0433 0.5341 0.6965
1.500 0.4076 0.00933 0.00288 -0.0435 0.5294 0.6974
1.750 0.4352 0.00939 0.00290 -0.0437 0.5251 0.6984
2.000 0.4629 0.00943 0.00294 -0.0439 0.5209 0.6993
2.250 0.4907 0.00946 0.00299 -0.0441 0.5162 0.7002
2.500 0.5181 0.00952 0.00305 -0.0442 0.5117 0.7012
2.750 0.5451 0.00960 0.00311 -0.0442 0.5073 0.7023
3.000 0.5729 0.00965 0.00319 -0.0444 0.5027 0.7034
3.250 0.6001 0.00971 0.00326 -0.0445 0.4977 0.7044
3.500 0.6268 0.00981 0.00333 -0.0445 0.4928 0.7055
3.750 0.6541 0.00986 0.00343 -0.0447 0.4875 0.7066
4.000 0.6809 0.00994 0.00351 -0.0447 0.4816 0.7077
4.250 0.7072 0.01005 0.00360 -0.0446 0.4760 0.7089
4.500 0.7341 0.01012 0.00371 -0.0447 0.4699 0.7101
4.750 0.7601 0.01022 0.00381 -0.0446 0.4637 0.7113
5.000 0.7865 0.01032 0.00393 -0.0446 0.4578 0.7124
5.250 0.8125 0.01042 0.00405 -0.0445 0.4511 0.7136
5.500 0.8378 0.01054 0.00418 -0.0443 0.4446 0.7148
5.750 0.8633 0.01064 0.00433 -0.0441 0.4370 0.7160
6.000 0.8877 0.01078 0.00449 -0.0437 0.4292 0.7173
6.250 0.9120 0.01091 0.00465 -0.0433 0.4194 0.7186
6.500 0.9360 0.01106 0.00482 -0.0428 0.4095 0.7199
6.750 0.9587 0.01125 0.00502 -0.0422 0.3985 0.7212
7.000 0.9804 0.01146 0.00523 -0.0413 0.3851 0.7227
7.250 1.0013 0.01170 0.00545 -0.0403 0.3702 0.7241
7.500 1.0210 0.01197 0.00571 -0.0392 0.3542 0.7257
7.750 1.0373 0.01234 0.00601 -0.0374 0.3324 0.7272
8.000 1.0497 0.01274 0.00634 -0.0349 0.3118 0.7288
8.250 1.0604 0.01321 0.00674 -0.0322 0.2890 0.7303
8.500 1.0691 0.01380 0.00725 -0.0292 0.2658 0.7319
8.750 1.0778 0.01442 0.00781 -0.0264 0.2433 0.7336
9.000 1.0850 0.01513 0.00845 -0.0234 0.2221 0.7356
9.250 1.0928 0.01584 0.00911 -0.0207 0.2027 0.7377
9.500 1.0999 0.01662 0.00984 -0.0181 0.1850 0.7399
9.750 1.1047 0.01754 0.01069 -0.0154 0.1668 0.7421
10.000 1.1108 0.01847 0.01157 -0.0129 0.1515 0.7441
10.250 1.1162 0.01949 0.01255 -0.0106 0.1361 0.7461
10.750 1.1281 0.02163 0.01469 -0.0066 0.1123 0.7503
11.000 1.1350 0.02275 0.01583 -0.0049 0.1028 0.7527
11.250 1.1400 0.02405 0.01712 -0.0032 0.0929 0.7552
11.500 1.1446 0.02544 0.01851 -0.0016 0.0840 0.7578
11.750 1.1500 0.02684 0.01992 -0.0002 0.0758 0.7604
12.000 1.1547 0.02833 0.02143 0.0011 0.0684 0.7628
12.250 1.1577 0.03000 0.02312 0.0024 0.0608 0.7657
12.500 1.1630 0.03155 0.02473 0.0034 0.0553 0.7689
12.750 1.1666 0.03330 0.02650 0.0044 0.0497 0.7724
13.000 1.1699 0.03515 0.02837 0.0053 0.0442 0.7758
13.250 1.1736 0.03699 0.03026 0.0061 0.0398 0.7793
13.500 1.1769 0.03893 0.03226 0.0067 0.0358 0.7831
13.750 1.1801 0.04096 0.03434 0.0073 0.0321 0.7871
14.000 1.1823 0.04316 0.03656 0.0077 0.0283 0.7913
14.250 1.1861 0.04523 0.03872 0.0080 0.0263 0.7956
14.500 1.1888 0.04749 0.04105 0.0082 0.0233 0.8006
14.750 1.1909 0.04986 0.04348 0.0083 0.0210 0.8060
15.000 1.1945 0.05213 0.04584 0.0084 0.0192 0.8119
15.500 1.1984 0.05717 0.05104 0.0082 0.0156 0.8264
15.750 1.2005 0.05975 0.05372 0.0080 0.0144 0.8360
16.000 1.2011 0.06251 0.05658 0.0077 0.0131 0.8476
16.250 1.2032 0.06505 0.05928 0.0075 0.0125 0.8655
16.500 1.2038 0.06801 0.06242 0.0069 0.0105 0.9075
16.750 1.2108 0.07129 0.06585 0.0044 0.0101 1.0000
17.000 1.2126 0.07430 0.06894 0.0035 0.0091 1.0000
17.250 1.2130 0.07752 0.07225 0.0026 0.0086 1.0000
17.500 1.2123 0.08096 0.07575 0.0016 0.0079 1.0000
17.750 1.2118 0.08444 0.07931 0.0004 0.0073 1.0000
18.000 1.2112 0.08799 0.08295 -0.0008 0.0067 1.0000
18.250 1.2094 0.09177 0.08681 -0.0022 0.0062 1.0000
18.500 1.2069 0.09570 0.09083 -0.0037 0.0059 1.0000
18.750 1.2038 0.09979 0.09499 -0.0053 0.0055 1.0000
19.000 1.2017 0.10379 0.09909 -0.0070 0.0052 1.0000
19.250 1.1982 0.10807 0.10348 -0.0089 0.0049 1.0000
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Polar data table (+)
Polar graphs
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