EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 540 AIRFOIL (e540-il) Reynolds number: 500,000 Max Cl/Cd: 82.52 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e540-il-500000-n5.txt Download as CSV file: xf-e540-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5478 0.07785 0.07545 -0.0722 1.0000 0.0036
-13.000 -0.5813 0.06858 0.06601 -0.0768 1.0000 0.0036
-12.750 -0.5975 0.06195 0.05921 -0.0810 0.9984 0.0035
-12.500 -0.6255 0.05445 0.05143 -0.0835 0.9896 0.0034
-12.250 -0.6486 0.04873 0.04543 -0.0838 0.9690 0.0034
-12.000 -0.6601 0.04275 0.03903 -0.0861 0.9548 0.0034
-11.750 -0.6546 0.03786 0.03372 -0.0893 0.9450 0.0033
-11.500 -0.6370 0.03364 0.02905 -0.0933 0.9361 0.0033
-11.250 -0.6111 0.03005 0.02501 -0.0973 0.9252 0.0033
-11.000 -0.5809 0.02767 0.02228 -0.1006 0.9114 0.0033
-10.750 -0.5557 0.02593 0.02024 -0.1021 0.8957 0.0033
-10.500 -0.5354 0.02464 0.01871 -0.1022 0.8810 0.0034
-10.250 -0.5174 0.02358 0.01745 -0.1015 0.8686 0.0034
-9.750 -0.4841 0.02181 0.01537 -0.0993 0.8477 0.0036
-9.500 -0.4679 0.02106 0.01447 -0.0981 0.8389 0.0036
-9.250 -0.4518 0.02036 0.01365 -0.0968 0.8304 0.0037
-9.000 -0.4364 0.01965 0.01282 -0.0954 0.8227 0.0038
-8.750 -0.4202 0.01907 0.01214 -0.0941 0.8155 0.0038
-8.500 -0.4045 0.01845 0.01143 -0.0926 0.8091 0.0041
-8.250 -0.3888 0.01786 0.01076 -0.0911 0.8029 0.0042
-8.000 -0.3717 0.01739 0.01021 -0.0899 0.7975 0.0042
-7.750 -0.3575 0.01675 0.00951 -0.0882 0.7916 0.0046
-7.250 -0.3239 0.01585 0.00849 -0.0855 0.7815 0.0059
-7.000 -0.3065 0.01546 0.00804 -0.0842 0.7765 0.0063
-6.500 -0.2730 0.01464 0.00713 -0.0813 0.7680 0.0085
-6.250 -0.2568 0.01424 0.00672 -0.0797 0.7638 0.0120
-6.000 -0.2413 0.01383 0.00631 -0.0780 0.7598 0.0181
-5.750 -0.2269 0.01340 0.00591 -0.0762 0.7560 0.0296
-5.500 -0.2147 0.01293 0.00552 -0.0740 0.7518 0.0473
-5.250 -0.2064 0.01246 0.00516 -0.0710 0.7477 0.0740
-5.000 -0.2004 0.01203 0.00485 -0.0675 0.7443 0.1087
-4.750 -0.1918 0.01148 0.00452 -0.0645 0.7410 0.1613
-4.500 -0.1850 0.01078 0.00413 -0.0614 0.7374 0.2381
-4.250 -0.1792 0.00992 0.00367 -0.0581 0.7338 0.3416
-4.000 -0.1793 0.00850 0.00294 -0.0541 0.7306 0.5141
-3.750 -0.1624 0.00812 0.00310 -0.0522 0.7278 0.6510
-3.500 -0.1347 0.00824 0.00317 -0.0523 0.7251 0.6768
-3.250 -0.1067 0.00843 0.00332 -0.0523 0.7224 0.6920
-3.000 -0.0786 0.00867 0.00348 -0.0524 0.7198 0.7044
-2.750 -0.0497 0.00908 0.00389 -0.0523 0.7174 0.7134
-2.500 -0.0214 0.00931 0.00405 -0.0525 0.7151 0.7204
-2.250 0.0070 0.00933 0.00405 -0.0528 0.7126 0.7218
-2.000 0.0352 0.00931 0.00398 -0.0531 0.7101 0.7228
-1.750 0.0634 0.00929 0.00391 -0.0535 0.7075 0.7237
-1.500 0.0917 0.00926 0.00383 -0.0538 0.7050 0.7246
-1.250 0.1202 0.00925 0.00376 -0.0543 0.7028 0.7256
-1.000 0.1488 0.00925 0.00370 -0.0547 0.7007 0.7267
-0.750 0.1768 0.00921 0.00365 -0.0551 0.6981 0.7276
-0.500 0.2050 0.00918 0.00359 -0.0555 0.6954 0.7286
-0.250 0.2332 0.00916 0.00354 -0.0559 0.6928 0.7295
0.000 0.2616 0.00915 0.00349 -0.0563 0.6902 0.7306
0.250 0.2902 0.00915 0.00343 -0.0568 0.6877 0.7317
0.500 0.3183 0.00913 0.00340 -0.0572 0.6847 0.7325
0.750 0.3459 0.00911 0.00339 -0.0574 0.6811 0.7331
1.000 0.3737 0.00910 0.00338 -0.0577 0.6775 0.7337
1.250 0.4017 0.00911 0.00337 -0.0580 0.6741 0.7343
1.500 0.4294 0.00912 0.00339 -0.0582 0.6704 0.7349
1.750 0.4566 0.00912 0.00341 -0.0584 0.6659 0.7355
2.000 0.4840 0.00913 0.00342 -0.0585 0.6615 0.7362
2.250 0.5114 0.00915 0.00345 -0.0587 0.6570 0.7370
2.500 0.5381 0.00916 0.00350 -0.0587 0.6517 0.7378
2.750 0.5651 0.00918 0.00352 -0.0588 0.6465 0.7386
3.000 0.5919 0.00919 0.00357 -0.0589 0.6411 0.7394
3.250 0.6183 0.00921 0.00361 -0.0589 0.6347 0.7402
3.500 0.6447 0.00923 0.00364 -0.0588 0.6283 0.7410
3.750 0.6706 0.00925 0.00369 -0.0587 0.6205 0.7418
4.000 0.6962 0.00929 0.00375 -0.0585 0.6122 0.7426
4.250 0.7209 0.00934 0.00379 -0.0582 0.6020 0.7435
4.500 0.7453 0.00939 0.00386 -0.0577 0.5897 0.7444
4.750 0.7685 0.00947 0.00393 -0.0571 0.5748 0.7452
5.000 0.7901 0.00958 0.00402 -0.0561 0.5543 0.7461
5.250 0.8079 0.00979 0.00413 -0.0543 0.5257 0.7471
5.500 0.8203 0.01013 0.00433 -0.0515 0.4890 0.7480
5.750 0.8301 0.01055 0.00460 -0.0483 0.4508 0.7489
6.000 0.8372 0.01097 0.00489 -0.0445 0.4174 0.7498
6.250 0.8444 0.01143 0.00523 -0.0408 0.3838 0.7507
6.500 0.8522 0.01199 0.00567 -0.0375 0.3504 0.7516
6.750 0.8602 0.01258 0.00614 -0.0342 0.3186 0.7527
7.000 0.8687 0.01319 0.00663 -0.0312 0.2885 0.7537
7.250 0.8766 0.01384 0.00716 -0.0282 0.2578 0.7548
7.500 0.8835 0.01458 0.00775 -0.0252 0.2257 0.7559
7.750 0.8907 0.01535 0.00839 -0.0224 0.1958 0.7570
8.000 0.8996 0.01610 0.00903 -0.0199 0.1709 0.7581
8.250 0.9099 0.01682 0.00968 -0.0178 0.1508 0.7593
8.500 0.9205 0.01758 0.01037 -0.0158 0.1315 0.7605
8.750 0.9315 0.01834 0.01108 -0.0139 0.1145 0.7615
9.000 0.9410 0.01919 0.01186 -0.0119 0.0972 0.7625
9.250 0.9523 0.01998 0.01263 -0.0102 0.0841 0.7634
9.500 0.9641 0.02078 0.01342 -0.0087 0.0727 0.7644
9.750 0.9757 0.02161 0.01424 -0.0071 0.0623 0.7654
10.000 0.9870 0.02249 0.01511 -0.0057 0.0527 0.7664
10.250 0.9981 0.02341 0.01602 -0.0042 0.0444 0.7675
10.500 1.0084 0.02441 0.01702 -0.0028 0.0365 0.7686
10.750 1.0200 0.02535 0.01797 -0.0015 0.0306 0.7697
11.000 1.0309 0.02636 0.01899 -0.0003 0.0256 0.7709
11.250 1.0426 0.02734 0.02000 0.0008 0.0225 0.7720
11.500 1.0525 0.02847 0.02112 0.0020 0.0184 0.7732
11.750 1.0649 0.02945 0.02218 0.0030 0.0170 0.7743
12.250 1.0848 0.03180 0.02460 0.0051 0.0129 0.7765
12.500 1.0960 0.03291 0.02579 0.0060 0.0115 0.7778
12.750 1.1060 0.03414 0.02709 0.0069 0.0103 0.7790
13.000 1.1143 0.03554 0.02854 0.0078 0.0085 0.7803
13.250 1.1238 0.03688 0.02996 0.0086 0.0074 0.7816
13.500 1.1324 0.03833 0.03148 0.0094 0.0064 0.7828
13.750 1.1398 0.03992 0.03313 0.0101 0.0057 0.7841
14.000 1.1463 0.04165 0.03492 0.0108 0.0051 0.7854
14.250 1.1531 0.04339 0.03677 0.0114 0.0048 0.7867
14.500 1.1600 0.04517 0.03863 0.0119 0.0042 0.7880
14.750 1.1647 0.04719 0.04072 0.0124 0.0036 0.7893
15.000 1.1690 0.04930 0.04293 0.0128 0.0034 0.7905
15.250 1.1703 0.05179 0.04553 0.0132 0.0030 0.7917
15.500 1.1732 0.05419 0.04805 0.0134 0.0030 0.7931
15.750 1.1755 0.05671 0.05069 0.0134 0.0030 0.7945
16.000 1.1778 0.05934 0.05347 0.0133 0.0027 0.7959
16.250 1.1781 0.06228 0.05653 0.0131 0.0027 0.7973
16.500 1.1777 0.06541 0.05979 0.0127 0.0026 0.7988
16.750 1.1768 0.06867 0.06318 0.0121 0.0025 0.8003
17.000 1.1744 0.07228 0.06691 0.0113 0.0025 0.8019
17.250 1.1717 0.07605 0.07081 0.0102 0.0023 0.8033
17.500 1.1677 0.08010 0.07500 0.0090 0.0022 0.8048
17.750 1.1628 0.08440 0.07944 0.0075 0.0022 0.8063
18.000 1.1561 0.08912 0.08431 0.0057 0.0022 0.8078
18.250 1.1486 0.09415 0.08948 0.0036 0.0021 0.8094
18.500 1.1413 0.09928 0.09475 0.0013 0.0021 0.8109
18.750 1.1317 0.10494 0.10055 -0.0014 0.0020 0.8123
19.000 1.1209 0.11095 0.10671 -0.0045 0.0020 0.8137
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