EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 540 AIRFOIL (e540-il) Reynolds number: 200,000 Max Cl/Cd: 57.01 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e540-il-200000-n5.txt Download as CSV file: xf-e540-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 540 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4722 0.08851 0.08501 -0.0693 1.0000 0.0079
-12.250 -0.5239 0.07429 0.07059 -0.0762 1.0000 0.0074
-12.000 -0.5683 0.06616 0.06224 -0.0772 1.0000 0.0072
-11.500 -0.6141 0.05371 0.04912 -0.0792 0.9874 0.0068
-11.250 -0.6235 0.04936 0.04448 -0.0798 0.9728 0.0069
-11.000 -0.6257 0.04546 0.04022 -0.0803 0.9610 0.0068
-10.750 -0.6212 0.04185 0.03625 -0.0812 0.9515 0.0068
-10.500 -0.6088 0.03847 0.03248 -0.0826 0.9444 0.0069
-10.250 -0.5921 0.03556 0.02922 -0.0837 0.9360 0.0069
-10.000 -0.5682 0.03301 0.02634 -0.0854 0.9294 0.0071
-9.750 -0.5426 0.03101 0.02409 -0.0869 0.9211 0.0073
-9.500 -0.5111 0.02909 0.02186 -0.0888 0.9150 0.0074
-9.250 -0.4821 0.02764 0.02021 -0.0901 0.9066 0.0078
-9.000 -0.4497 0.02621 0.01858 -0.0917 0.9001 0.0083
-8.750 -0.4221 0.02509 0.01730 -0.0923 0.8919 0.0086
-8.500 -0.3941 0.02405 0.01610 -0.0931 0.8850 0.0095
-8.250 -0.3721 0.02311 0.01505 -0.0928 0.8767 0.0107
-8.000 -0.3511 0.02232 0.01418 -0.0926 0.8691 0.0113
-7.750 -0.3309 0.02173 0.01350 -0.0920 0.8612 0.0129
-7.500 -0.3132 0.02103 0.01268 -0.0909 0.8542 0.0143
-7.250 -0.2988 0.02025 0.01180 -0.0893 0.8470 0.0158
-7.000 -0.2830 0.01960 0.01108 -0.0879 0.8411 0.0179
-6.750 -0.2674 0.01907 0.01049 -0.0863 0.8347 0.0225
-6.500 -0.2523 0.01844 0.00983 -0.0847 0.8295 0.0311
-6.250 -0.2419 0.01777 0.00926 -0.0824 0.8232 0.0481
-5.750 -0.2260 0.01632 0.00817 -0.0770 0.8124 0.1303
-5.500 -0.2268 0.01557 0.00769 -0.0728 0.8066 0.1881
-5.250 -0.2339 0.01475 0.00719 -0.0674 0.8016 0.2645
-5.000 -0.2444 0.01373 0.00667 -0.0615 0.7959 0.3695
-4.750 -0.2339 0.01421 0.00854 -0.0560 0.7919 0.6170
-4.500 -0.2186 0.01421 0.00840 -0.0541 0.7881 0.6622
-4.250 -0.1949 0.01460 0.00865 -0.0531 0.7850 0.6824
-4.000 -0.1707 0.01517 0.00912 -0.0520 0.7812 0.6975
-3.750 -0.1407 0.01612 0.00997 -0.0513 0.7781 0.7109
-3.500 -0.1045 0.01748 0.01126 -0.0511 0.7754 0.7236
-3.250 -0.0804 0.01778 0.01143 -0.0503 0.7727 0.7337
-3.000 -0.0531 0.01789 0.01146 -0.0501 0.7695 0.7353
-2.750 -0.0276 0.01790 0.01139 -0.0499 0.7663 0.7369
-2.500 -0.0025 0.01784 0.01124 -0.0496 0.7632 0.7391
-2.250 0.0209 0.01766 0.01096 -0.0493 0.7603 0.7422
-2.000 0.0400 0.01719 0.01036 -0.0488 0.7577 0.7475
-1.750 0.0637 0.01718 0.01032 -0.0482 0.7542 0.7486
-1.500 0.0888 0.01715 0.01025 -0.0479 0.7511 0.7498
-1.250 0.1146 0.01709 0.01013 -0.0479 0.7482 0.7511
-1.000 0.1412 0.01700 0.00997 -0.0480 0.7456 0.7526
-0.750 0.1680 0.01689 0.00980 -0.0483 0.7435 0.7544
-0.500 0.1889 0.01675 0.00966 -0.0476 0.7398 0.7565
-0.250 0.2113 0.01653 0.00939 -0.0473 0.7364 0.7595
0.000 0.2364 0.01632 0.00912 -0.0475 0.7335 0.7615
0.250 0.2642 0.01626 0.00903 -0.0479 0.7311 0.7623
0.500 0.2910 0.01624 0.00900 -0.0480 0.7284 0.7632
0.750 0.3136 0.01625 0.00904 -0.0473 0.7246 0.7643
1.000 0.3388 0.01620 0.00900 -0.0472 0.7210 0.7654
1.250 0.3661 0.01613 0.00891 -0.0475 0.7180 0.7664
1.500 0.3952 0.01605 0.00881 -0.0481 0.7154 0.7674
1.750 0.4165 0.01604 0.00884 -0.0473 0.7107 0.7689
2.000 0.4416 0.01598 0.00880 -0.0473 0.7065 0.7705
2.250 0.4700 0.01587 0.00868 -0.0478 0.7030 0.7719
2.500 0.4961 0.01579 0.00862 -0.0480 0.6989 0.7732
2.750 0.5197 0.01572 0.00858 -0.0478 0.6936 0.7747
3.000 0.5479 0.01561 0.00848 -0.0482 0.6891 0.7757
3.250 0.5728 0.01559 0.00852 -0.0479 0.6840 0.7764
3.500 0.5960 0.01557 0.00856 -0.0473 0.6778 0.7773
3.750 0.6250 0.01549 0.00850 -0.0477 0.6731 0.7783
4.000 0.6451 0.01550 0.00861 -0.0465 0.6658 0.7794
4.250 0.6723 0.01542 0.00857 -0.0466 0.6598 0.7803
4.500 0.6936 0.01540 0.00865 -0.0456 0.6519 0.7814
4.750 0.7207 0.01531 0.00857 -0.0457 0.6447 0.7824
5.000 0.7405 0.01530 0.00867 -0.0445 0.6351 0.7836
5.250 0.7634 0.01525 0.00869 -0.0438 0.6254 0.7848
5.500 0.7866 0.01519 0.00868 -0.0432 0.6145 0.7861
5.750 0.8081 0.01515 0.00869 -0.0423 0.6018 0.7875
6.000 0.8273 0.01514 0.00873 -0.0409 0.5863 0.7892
6.250 0.8442 0.01516 0.00880 -0.0390 0.5669 0.7903
6.500 0.8604 0.01520 0.00886 -0.0369 0.5431 0.7913
6.750 0.8722 0.01530 0.00890 -0.0339 0.5129 0.7923
7.000 0.8799 0.01556 0.00902 -0.0303 0.4780 0.7936
7.250 0.8850 0.01603 0.00933 -0.0265 0.4418 0.7949
7.500 0.8886 0.01668 0.00982 -0.0226 0.4058 0.7964
7.750 0.8920 0.01741 0.01041 -0.0190 0.3720 0.7980
8.000 0.8945 0.01825 0.01111 -0.0155 0.3375 0.7996
8.250 0.8973 0.01917 0.01189 -0.0123 0.3054 0.8014
8.500 0.9008 0.02017 0.01277 -0.0094 0.2744 0.8033
8.750 0.9042 0.02117 0.01369 -0.0066 0.2452 0.8047
9.000 0.9079 0.02225 0.01467 -0.0039 0.2164 0.8060
9.250 0.9126 0.02337 0.01568 -0.0016 0.1897 0.8073
9.500 0.9181 0.02452 0.01674 0.0005 0.1642 0.8087
9.750 0.9255 0.02563 0.01779 0.0022 0.1419 0.8101
10.250 0.9419 0.02793 0.02000 0.0052 0.1060 0.8131
10.500 0.9507 0.02911 0.02115 0.0065 0.0907 0.8146
10.750 0.9590 0.03037 0.02237 0.0078 0.0762 0.8162
11.000 0.9679 0.03164 0.02366 0.0089 0.0653 0.8177
11.250 0.9755 0.03293 0.02499 0.0103 0.0564 0.8190
11.500 0.9827 0.03430 0.02638 0.0115 0.0486 0.8206
11.750 0.9911 0.03564 0.02779 0.0126 0.0422 0.8222
12.000 0.9967 0.03725 0.02941 0.0138 0.0368 0.8240
12.250 1.0055 0.03866 0.03094 0.0147 0.0329 0.8257
12.500 1.0124 0.04026 0.03260 0.0155 0.0292 0.8274
12.750 1.0171 0.04212 0.03451 0.0163 0.0260 0.8291
13.000 1.0255 0.04372 0.03624 0.0169 0.0235 0.8309
13.250 1.0320 0.04547 0.03807 0.0175 0.0209 0.8325
13.500 1.0326 0.04781 0.04046 0.0183 0.0186 0.8340
13.750 1.0392 0.04967 0.04252 0.0187 0.0171 0.8357
14.000 1.0445 0.05172 0.04470 0.0191 0.0156 0.8375
14.250 1.0488 0.05393 0.04700 0.0192 0.0139 0.8394
14.500 1.0463 0.05697 0.05011 0.0194 0.0126 0.8414
14.750 1.0501 0.05944 0.05276 0.0194 0.0116 0.8434
15.000 1.0515 0.06228 0.05575 0.0193 0.0109 0.8455
15.250 1.0519 0.06522 0.05885 0.0191 0.0101 0.8474
15.500 1.0517 0.06834 0.06211 0.0186 0.0095 0.8496
15.750 1.0503 0.07171 0.06562 0.0180 0.0092 0.8519
16.000 1.0463 0.07558 0.06961 0.0171 0.0086 0.8543
16.250 1.0384 0.08010 0.07426 0.0159 0.0082 0.8565
16.500 1.0372 0.08389 0.07822 0.0147 0.0079 0.8590
16.750 1.0355 0.08778 0.08231 0.0133 0.0075 0.8613
17.000 1.0303 0.09229 0.08700 0.0117 0.0074 0.8636
17.250 1.0267 0.09675 0.09165 0.0097 0.0068 0.8663
17.500 1.0211 0.10162 0.09669 0.0075 0.0065 0.8691
17.750 1.0142 0.10684 0.10207 0.0050 0.0064 0.8719
18.000 1.0069 0.11227 0.10767 0.0022 0.0061 0.8748
18.250 0.9984 0.11801 0.11359 -0.0007 0.0060 0.8780
18.500 0.9906 0.12375 0.11950 -0.0039 0.0058 0.8818
18.750 0.9812 0.12993 0.12583 -0.0074 0.0057 0.8859
19.000 0.9702 0.13651 0.13257 -0.0111 0.0057 0.8902
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