EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 544 AIRFOIL (e544-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.07 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e544-il-1000000-n5.txt Download as CSV file: xf-e544-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 544 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.5936 0.12789 0.12598 -0.0414 1.0000 0.0022
-16.500 -0.6983 0.09898 0.09680 -0.0540 1.0000 0.0021
-16.250 -0.7488 0.08314 0.08071 -0.0627 1.0000 0.0021
-16.000 -0.7775 0.07368 0.07106 -0.0680 1.0000 0.0021
-15.750 -0.7907 0.06790 0.06516 -0.0708 1.0000 0.0020
-15.500 -0.8187 0.06059 0.05763 -0.0735 1.0000 0.0021
-15.250 -0.8244 0.05696 0.05391 -0.0744 1.0000 0.0020
-15.000 -0.8459 0.05171 0.04845 -0.0750 1.0000 0.0020
-14.750 -0.8481 0.04904 0.04569 -0.0750 1.0000 0.0020
-14.500 -0.8593 0.04557 0.04205 -0.0744 1.0000 0.0020
-14.250 -0.8643 0.04296 0.03931 -0.0736 1.0000 0.0020
-14.000 -0.8721 0.04019 0.03639 -0.0723 1.0000 0.0020
-13.750 -0.8740 0.03810 0.03418 -0.0710 1.0000 0.0020
-13.250 -0.8505 0.03373 0.02953 -0.0732 0.9968 0.0020
-13.000 -0.8481 0.03172 0.02739 -0.0718 0.9862 0.0021
-12.750 -0.8310 0.03003 0.02557 -0.0729 0.9612 0.0021
-12.500 -0.7945 0.02787 0.02322 -0.0784 0.9488 0.0021
-12.250 -0.7474 0.02592 0.02108 -0.0857 0.9381 0.0021
-12.000 -0.6940 0.02415 0.01911 -0.0940 0.9231 0.0021
-11.750 -0.6542 0.02290 0.01763 -0.0989 0.8935 0.0022
-11.500 -0.6364 0.02221 0.01677 -0.0986 0.8667 0.0022
-11.250 -0.6243 0.02145 0.01585 -0.0972 0.8470 0.0022
-11.000 -0.6117 0.02075 0.01502 -0.0957 0.8311 0.0022
-10.750 -0.5989 0.02006 0.01422 -0.0942 0.8175 0.0022
-10.500 -0.5848 0.01945 0.01352 -0.0928 0.8053 0.0023
-10.250 -0.5706 0.01887 0.01285 -0.0914 0.7936 0.0023
-10.000 -0.5561 0.01830 0.01218 -0.0900 0.7832 0.0023
-9.750 -0.5399 0.01780 0.01162 -0.0888 0.7745 0.0023
-9.250 -0.5125 0.01656 0.01023 -0.0856 0.7577 0.0025
-9.000 -0.4984 0.01600 0.00959 -0.0840 0.7495 0.0026
-8.750 -0.4820 0.01555 0.00910 -0.0827 0.7420 0.0027
-8.500 -0.4664 0.01510 0.00859 -0.0812 0.7342 0.0029
-8.250 -0.4498 0.01469 0.00813 -0.0799 0.7275 0.0030
-8.000 -0.4334 0.01428 0.00768 -0.0785 0.7206 0.0033
-7.750 -0.4175 0.01388 0.00723 -0.0770 0.7147 0.0036
-7.500 -0.4010 0.01350 0.00681 -0.0756 0.7087 0.0039
-7.250 -0.3854 0.01313 0.00639 -0.0740 0.7027 0.0039
-7.000 -0.3715 0.01274 0.00596 -0.0720 0.6973 0.0042
-6.750 -0.3592 0.01240 0.00560 -0.0697 0.6913 0.0049
-6.500 -0.3463 0.01218 0.00533 -0.0673 0.6856 0.0055
-6.250 -0.3282 0.01194 0.00506 -0.0658 0.6806 0.0061
-6.000 -0.3092 0.01168 0.00479 -0.0645 0.6756 0.0079
-5.750 -0.2896 0.01145 0.00454 -0.0634 0.6709 0.0102
-5.500 -0.2689 0.01121 0.00430 -0.0624 0.6667 0.0136
-5.250 -0.2478 0.01096 0.00406 -0.0615 0.6621 0.0200
-5.000 -0.2269 0.01070 0.00383 -0.0605 0.6573 0.0306
-4.750 -0.2063 0.01042 0.00361 -0.0595 0.6528 0.0468
-4.500 -0.1862 0.01003 0.00335 -0.0586 0.6489 0.0785
-4.250 -0.1669 0.00957 0.00309 -0.0575 0.6449 0.1292
-4.000 -0.1501 0.00891 0.00275 -0.0561 0.6410 0.2135
-3.500 -0.1173 0.00712 0.00188 -0.0535 0.6336 0.4659
-3.250 -0.0960 0.00648 0.00166 -0.0528 0.6298 0.5854
-3.000 -0.0684 0.00646 0.00168 -0.0529 0.6259 0.6165
-2.750 -0.0402 0.00651 0.00170 -0.0531 0.6224 0.6331
-2.500 -0.0114 0.00658 0.00174 -0.0534 0.6194 0.6448
-2.250 0.0173 0.00666 0.00183 -0.0537 0.6161 0.6544
-2.000 0.0462 0.00675 0.00185 -0.0540 0.6124 0.6604
-1.750 0.0747 0.00676 0.00182 -0.0544 0.6089 0.6616
-1.250 0.1321 0.00676 0.00176 -0.0551 0.6029 0.6634
-1.000 0.1610 0.00677 0.00175 -0.0555 0.5998 0.6644
-0.750 0.1897 0.00678 0.00174 -0.0558 0.5964 0.6654
-0.500 0.2182 0.00681 0.00173 -0.0561 0.5932 0.6663
0.000 0.2754 0.00685 0.00173 -0.0568 0.5871 0.6679
0.250 0.3042 0.00687 0.00174 -0.0572 0.5840 0.6688
0.500 0.3327 0.00690 0.00175 -0.0576 0.5803 0.6697
0.750 0.3608 0.00694 0.00176 -0.0578 0.5762 0.6705
1.000 0.3891 0.00697 0.00178 -0.0581 0.5720 0.6714
1.250 0.4176 0.00700 0.00180 -0.0584 0.5673 0.6725
1.500 0.4457 0.00704 0.00182 -0.0587 0.5628 0.6735
1.750 0.4734 0.00710 0.00186 -0.0589 0.5586 0.6744
2.000 0.5020 0.00713 0.00189 -0.0593 0.5546 0.6751
2.250 0.5301 0.00717 0.00192 -0.0595 0.5493 0.6758
2.500 0.5575 0.00724 0.00197 -0.0597 0.5441 0.6765
2.750 0.5855 0.00727 0.00201 -0.0599 0.5392 0.6773
3.000 0.6132 0.00731 0.00206 -0.0601 0.5336 0.6783
3.250 0.6400 0.00738 0.00212 -0.0601 0.5274 0.6792
3.500 0.6678 0.00742 0.00219 -0.0604 0.5209 0.6801
3.750 0.6943 0.00751 0.00226 -0.0603 0.5126 0.6810
4.000 0.7214 0.00758 0.00234 -0.0604 0.5043 0.6819
4.250 0.7473 0.00768 0.00243 -0.0603 0.4940 0.6829
4.500 0.7731 0.00780 0.00253 -0.0601 0.4823 0.6839
4.750 0.7982 0.00793 0.00264 -0.0598 0.4683 0.6851
5.000 0.8217 0.00813 0.00278 -0.0592 0.4500 0.6862
5.250 0.8443 0.00837 0.00294 -0.0585 0.4272 0.6873
5.500 0.8645 0.00870 0.00316 -0.0573 0.3992 0.6883
5.750 0.8830 0.00908 0.00342 -0.0559 0.3685 0.6893
6.000 0.9014 0.00946 0.00368 -0.0544 0.3418 0.6902
6.250 0.9195 0.00984 0.00396 -0.0529 0.3159 0.6911
6.500 0.9364 0.01022 0.00424 -0.0511 0.2919 0.6920
6.750 0.9504 0.01060 0.00452 -0.0488 0.2681 0.6928
7.000 0.9641 0.01095 0.00481 -0.0464 0.2484 0.6941
7.250 0.9765 0.01138 0.00516 -0.0439 0.2255 0.6953
7.500 0.9880 0.01188 0.00557 -0.0413 0.2040 0.6965
7.750 1.0009 0.01233 0.00596 -0.0389 0.1854 0.6977
8.000 1.0117 0.01287 0.00642 -0.0363 0.1654 0.6990
8.250 1.0228 0.01340 0.00690 -0.0338 0.1488 0.7005
8.500 1.0330 0.01399 0.00742 -0.0313 0.1328 0.7019
8.750 1.0441 0.01457 0.00796 -0.0290 0.1196 0.7033
9.000 1.0551 0.01518 0.00853 -0.0269 0.1073 0.7046
9.250 1.0665 0.01580 0.00913 -0.0248 0.0971 0.7058
9.500 1.0767 0.01651 0.00981 -0.0227 0.0868 0.7070
9.750 1.0866 0.01727 0.01054 -0.0207 0.0773 0.7080
10.000 1.0951 0.01814 0.01137 -0.0186 0.0672 0.7092
10.250 1.1048 0.01897 0.01220 -0.0168 0.0591 0.7107
10.500 1.1143 0.01987 0.01309 -0.0150 0.0514 0.7121
10.750 1.1240 0.02079 0.01402 -0.0134 0.0456 0.7136
11.000 1.1322 0.02184 0.01506 -0.0117 0.0391 0.7151
11.250 1.1415 0.02286 0.01608 -0.0102 0.0340 0.7166
11.500 1.1509 0.02391 0.01715 -0.0088 0.0298 0.7182
11.750 1.1596 0.02505 0.01829 -0.0075 0.0262 0.7197
12.000 1.1671 0.02629 0.01954 -0.0061 0.0219 0.7213
12.250 1.1767 0.02744 0.02071 -0.0050 0.0192 0.7230
12.500 1.1852 0.02870 0.02199 -0.0039 0.0169 0.7244
12.750 1.1921 0.03008 0.02339 -0.0027 0.0140 0.7262
13.000 1.2020 0.03130 0.02466 -0.0019 0.0129 0.7280
13.250 1.2083 0.03281 0.02620 -0.0009 0.0103 0.7298
13.500 1.2174 0.03417 0.02761 -0.0001 0.0096 0.7317
13.750 1.2251 0.03566 0.02914 0.0006 0.0083 0.7336
14.000 1.2334 0.03715 0.03068 0.0013 0.0076 0.7355
14.250 1.2392 0.03889 0.03246 0.0019 0.0061 0.7374
14.500 1.2470 0.04050 0.03412 0.0024 0.0056 0.7392
15.000 1.2602 0.04405 0.03779 0.0033 0.0046 0.7431
15.250 1.2669 0.04588 0.03969 0.0036 0.0041 0.7454
15.500 1.2724 0.04788 0.04175 0.0038 0.0038 0.7477
15.750 1.2769 0.05001 0.04395 0.0040 0.0034 0.7501
16.000 1.2826 0.05207 0.04608 0.0041 0.0031 0.7526
16.250 1.2870 0.05432 0.04840 0.0040 0.0028 0.7551
16.750 1.2948 0.05909 0.05333 0.0038 0.0025 0.7607
17.000 1.2966 0.06177 0.05609 0.0035 0.0022 0.7640
17.250 1.3003 0.06430 0.05871 0.0031 0.0021 0.7673
17.500 1.3022 0.06714 0.06164 0.0026 0.0019 0.7705
18.000 1.3051 0.07305 0.06774 0.0013 0.0018 0.7773
18.250 1.3054 0.07626 0.07105 0.0004 0.0017 0.7812
18.500 1.3035 0.07984 0.07473 -0.0006 0.0015 0.7850
19.000 1.2995 0.08729 0.08238 -0.0031 0.0014 0.7934
19.250 1.2967 0.09123 0.08643 -0.0046 0.0013 0.7983
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Polar data table (+)
Polar graphs
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