EPPLER 603 AIRFOIL (e603-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 603 AIRFOIL (e603-il) Reynolds number: 500,000 Max Cl/Cd: 103.17 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e603-il-500000-n5.txt Download as CSV file: xf-e603-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 603 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.5752 0.10955 0.10668 -0.0639 1.0000 0.0078
-16.750 -0.6272 0.09473 0.09164 -0.0716 1.0000 0.0077
-16.500 -0.6532 0.08558 0.08234 -0.0767 1.0000 0.0077
-16.250 -0.6798 0.07533 0.07188 -0.0834 0.9896 0.0077
-16.000 -0.6797 0.06639 0.06267 -0.0942 0.9515 0.0077
-15.750 -0.6638 0.05723 0.05313 -0.1088 0.9153 0.0077
-15.500 -0.6474 0.05168 0.04697 -0.1177 0.8396 0.0078
-15.250 -0.6561 0.04843 0.04342 -0.1180 0.8052 0.0078
-15.000 -0.6606 0.04569 0.04044 -0.1180 0.7845 0.0079
-14.750 -0.6629 0.04323 0.03776 -0.1179 0.7691 0.0079
-14.250 -0.6643 0.03886 0.03307 -0.1170 0.7463 0.0080
-14.000 -0.6645 0.03687 0.03093 -0.1163 0.7375 0.0082
-13.750 -0.6613 0.03518 0.02911 -0.1155 0.7296 0.0082
-13.500 -0.6576 0.03359 0.02739 -0.1146 0.7223 0.0083
-13.250 -0.6505 0.03229 0.02599 -0.1137 0.7160 0.0084
-13.000 -0.6428 0.03104 0.02464 -0.1128 0.7096 0.0085
-12.500 -0.6241 0.02885 0.02225 -0.1108 0.6987 0.0088
-12.250 -0.6134 0.02784 0.02115 -0.1098 0.6935 0.0089
-12.000 -0.6020 0.02690 0.02011 -0.1088 0.6889 0.0091
-11.750 -0.5901 0.02600 0.01912 -0.1077 0.6851 0.0092
-11.500 -0.5772 0.02514 0.01818 -0.1067 0.6814 0.0094
-11.250 -0.5632 0.02436 0.01732 -0.1057 0.6777 0.0097
-11.000 -0.5499 0.02356 0.01642 -0.1045 0.6742 0.0098
-10.750 -0.5362 0.02280 0.01557 -0.1034 0.6710 0.0100
-10.500 -0.5204 0.02218 0.01487 -0.1024 0.6681 0.0102
-10.250 -0.5044 0.02154 0.01417 -0.1014 0.6653 0.0103
-10.000 -0.4907 0.02078 0.01339 -0.1002 0.6624 0.0108
-9.750 -0.4745 0.02019 0.01275 -0.0991 0.6594 0.0111
-9.500 -0.4574 0.01968 0.01218 -0.0982 0.6566 0.0115
-9.250 -0.4402 0.01919 0.01163 -0.0971 0.6539 0.0119
-9.000 -0.4226 0.01871 0.01108 -0.0961 0.6516 0.0126
-8.750 -0.4054 0.01819 0.01053 -0.0950 0.6495 0.0129
-8.500 -0.3885 0.01766 0.00998 -0.0939 0.6474 0.0134
-8.250 -0.3710 0.01720 0.00950 -0.0928 0.6452 0.0140
-8.000 -0.3532 0.01677 0.00903 -0.0917 0.6431 0.0147
-7.750 -0.3353 0.01637 0.00858 -0.0905 0.6410 0.0158
-7.500 -0.3185 0.01596 0.00815 -0.0892 0.6391 0.0166
-7.250 -0.3023 0.01561 0.00777 -0.0877 0.6372 0.0179
-6.750 -0.2703 0.01499 0.00710 -0.0846 0.6336 0.0218
-6.500 -0.2509 0.01466 0.00677 -0.0837 0.6317 0.0246
-6.250 -0.2303 0.01436 0.00647 -0.0829 0.6298 0.0280
-6.000 -0.2093 0.01406 0.00618 -0.0822 0.6281 0.0327
-5.750 -0.1877 0.01377 0.00590 -0.0816 0.6263 0.0385
-5.500 -0.1655 0.01350 0.00564 -0.0810 0.6247 0.0465
-5.250 -0.1432 0.01320 0.00540 -0.0805 0.6231 0.0587
-5.000 -0.1203 0.01292 0.00516 -0.0801 0.6215 0.0739
-4.750 -0.0975 0.01261 0.00492 -0.0797 0.6198 0.0952
-4.500 -0.0746 0.01227 0.00469 -0.0794 0.6181 0.1258
-4.250 -0.0513 0.01187 0.00446 -0.0792 0.6166 0.1651
-4.000 -0.0277 0.01143 0.00422 -0.0792 0.6152 0.2158
-3.750 -0.0038 0.01091 0.00395 -0.0793 0.6137 0.2824
-3.500 0.0198 0.01011 0.00358 -0.0797 0.6120 0.3908
-3.250 0.0446 0.00899 0.00323 -0.0805 0.6103 0.5806
-3.000 0.0731 0.00901 0.00340 -0.0807 0.6085 0.6347
-2.750 0.1026 0.00910 0.00346 -0.0811 0.6070 0.6524
-2.500 0.1323 0.00917 0.00347 -0.0816 0.6055 0.6641
-2.250 0.1619 0.00928 0.00352 -0.0821 0.6039 0.6747
-2.000 0.1912 0.00945 0.00365 -0.0824 0.6023 0.6843
-1.750 0.2209 0.00965 0.00380 -0.0828 0.6008 0.6957
-1.500 0.2490 0.00992 0.00411 -0.0826 0.5994 0.7041
-1.250 0.2791 0.01004 0.00416 -0.0833 0.5977 0.7106
-1.000 0.3080 0.01006 0.00417 -0.0836 0.5959 0.7121
-0.750 0.3371 0.01007 0.00417 -0.0841 0.5942 0.7133
-0.500 0.3662 0.01010 0.00417 -0.0845 0.5925 0.7144
-0.250 0.3954 0.01012 0.00416 -0.0850 0.5907 0.7155
0.000 0.4246 0.01014 0.00415 -0.0855 0.5890 0.7166
0.250 0.4539 0.01018 0.00416 -0.0860 0.5873 0.7178
0.500 0.4833 0.01024 0.00417 -0.0865 0.5856 0.7192
0.750 0.5125 0.01026 0.00419 -0.0870 0.5840 0.7204
1.000 0.5416 0.01027 0.00420 -0.0876 0.5821 0.7216
1.250 0.5708 0.01029 0.00422 -0.0881 0.5801 0.7228
1.500 0.5999 0.01031 0.00424 -0.0886 0.5780 0.7242
1.750 0.6291 0.01034 0.00426 -0.0892 0.5759 0.7255
2.000 0.6583 0.01037 0.00426 -0.0897 0.5738 0.7267
2.250 0.6875 0.01040 0.00427 -0.0903 0.5717 0.7276
2.500 0.7163 0.01045 0.00430 -0.0908 0.5696 0.7285
2.750 0.7447 0.01048 0.00436 -0.0911 0.5675 0.7293
3.000 0.7728 0.01051 0.00444 -0.0915 0.5648 0.7302
3.250 0.8008 0.01054 0.00451 -0.0918 0.5620 0.7312
3.500 0.8288 0.01058 0.00457 -0.0920 0.5592 0.7322
3.750 0.8568 0.01063 0.00463 -0.0923 0.5564 0.7332
4.000 0.8849 0.01068 0.00467 -0.0927 0.5536 0.7342
4.250 0.9124 0.01073 0.00477 -0.0929 0.5502 0.7351
4.500 0.9398 0.01076 0.00485 -0.0931 0.5458 0.7361
4.750 0.9669 0.01080 0.00491 -0.0933 0.5414 0.7372
5.000 0.9938 0.01086 0.00495 -0.0934 0.5374 0.7383
5.250 1.0208 0.01091 0.00508 -0.0935 0.5323 0.7395
5.500 1.0473 0.01097 0.00516 -0.0936 0.5269 0.7408
5.750 1.0732 0.01105 0.00524 -0.0935 0.5216 0.7419
6.000 1.0994 0.01112 0.00536 -0.0936 0.5151 0.7429
6.250 1.1242 0.01122 0.00546 -0.0933 0.5080 0.7439
6.500 1.1493 0.01132 0.00560 -0.0931 0.4999 0.7448
6.750 1.1719 0.01145 0.00573 -0.0925 0.4910 0.7457
7.000 1.1947 0.01159 0.00590 -0.0919 0.4805 0.7466
7.250 1.2153 0.01178 0.00609 -0.0909 0.4689 0.7476
7.500 1.2335 0.01203 0.00633 -0.0894 0.4558 0.7487
7.750 1.2481 0.01234 0.00661 -0.0873 0.4411 0.7500
8.000 1.2588 0.01269 0.00693 -0.0845 0.4254 0.7513
8.250 1.2686 0.01316 0.00736 -0.0817 0.4090 0.7526
8.500 1.2775 0.01371 0.00787 -0.0789 0.3924 0.7539
8.750 1.2840 0.01437 0.00849 -0.0758 0.3745 0.7553
9.000 1.2890 0.01514 0.00921 -0.0727 0.3571 0.7566
9.250 1.2912 0.01608 0.01010 -0.0694 0.3390 0.7580
9.500 1.2916 0.01722 0.01118 -0.0661 0.3214 0.7594
10.250 1.2892 0.02168 0.01551 -0.0579 0.2703 0.7634
10.500 1.2882 0.02343 0.01724 -0.0556 0.2545 0.7648
10.750 1.2886 0.02520 0.01898 -0.0537 0.2404 0.7662
11.000 1.2880 0.02711 0.02086 -0.0518 0.2256 0.7675
11.250 1.2909 0.02884 0.02258 -0.0504 0.2135 0.7687
11.500 1.2935 0.03063 0.02437 -0.0490 0.2015 0.7700
11.750 1.2944 0.03259 0.02630 -0.0476 0.1882 0.7713
12.000 1.2968 0.03451 0.02820 -0.0464 0.1771 0.7726
12.250 1.2966 0.03668 0.03032 -0.0451 0.1626 0.7739
12.500 1.2982 0.03876 0.03236 -0.0441 0.1500 0.7752
12.750 1.2994 0.04097 0.03453 -0.0431 0.1372 0.7764
13.000 1.3013 0.04316 0.03668 -0.0423 0.1251 0.7776
13.250 1.3054 0.04523 0.03873 -0.0417 0.1144 0.7787
13.500 1.3092 0.04735 0.04083 -0.0411 0.1046 0.7799
13.750 1.3139 0.04944 0.04294 -0.0407 0.0973 0.7811
14.000 1.3193 0.05150 0.04501 -0.0403 0.0897 0.7824
14.250 1.3242 0.05365 0.04719 -0.0400 0.0833 0.7839
14.500 1.3284 0.05592 0.04946 -0.0397 0.0761 0.7854
14.750 1.3341 0.05810 0.05168 -0.0395 0.0706 0.7870
15.000 1.3383 0.06047 0.05405 -0.0394 0.0649 0.7885
15.250 1.3439 0.06273 0.05636 -0.0394 0.0600 0.7899
15.500 1.3478 0.06524 0.05887 -0.0394 0.0552 0.7913
15.750 1.3530 0.06764 0.06132 -0.0396 0.0508 0.7928
16.000 1.3564 0.07029 0.06399 -0.0398 0.0469 0.7941
16.500 1.3633 0.07569 0.06948 -0.0403 0.0392 0.7968
16.750 1.3672 0.07840 0.07224 -0.0407 0.0357 0.7982
17.000 1.3691 0.08142 0.07531 -0.0412 0.0327 0.7998
17.250 1.3720 0.08433 0.07828 -0.0417 0.0298 0.8014
17.500 1.3736 0.08748 0.08149 -0.0424 0.0274 0.8030
17.750 1.3754 0.09062 0.08469 -0.0431 0.0248 0.8047
18.000 1.3761 0.09397 0.08811 -0.0439 0.0227 0.8064
18.250 1.3769 0.09736 0.09156 -0.0448 0.0207 0.8081
18.500 1.3772 0.10086 0.09512 -0.0459 0.0191 0.8098
18.750 1.3772 0.10446 0.09879 -0.0470 0.0175 0.8115
19.000 1.3765 0.10813 0.10254 -0.0482 0.0164 0.8132
19.250 1.3761 0.11182 0.10632 -0.0495 0.0154 0.8152
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