EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 554 AIRFOIL (e554-il) Reynolds number: 500,000 Max Cl/Cd: 98.79 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e554-il-500000-n5.txt Download as CSV file: xf-e554-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 554 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
------ -------- --------- --------- -------- -------- --------
-19.000 -0.7064 0.14425 0.14106 -0.0229 1.0000 0.0051
-18.750 -0.7226 0.13637 0.13307 -0.0269 1.0000 0.0050
-18.500 -0.7379 0.12894 0.12552 -0.0306 1.0000 0.0050
-18.250 -0.7550 0.12133 0.11778 -0.0344 1.0000 0.0051
-18.000 -0.7657 0.11525 0.11161 -0.0374 1.0000 0.0050
-17.750 -0.7762 0.10929 0.10554 -0.0403 1.0000 0.0050
-17.500 -0.7882 0.10329 0.09943 -0.0431 1.0000 0.0050
-17.250 -0.7976 0.09779 0.09380 -0.0458 1.0000 0.0052
-17.000 -0.8052 0.09287 0.08881 -0.0480 1.0000 0.0050
-16.750 -0.8113 0.08818 0.08400 -0.0502 1.0000 0.0051
-16.500 -0.8193 0.08346 0.07919 -0.0522 1.0000 0.0051
-16.250 -0.8230 0.07942 0.07505 -0.0539 1.0000 0.0052
-16.000 -0.8267 0.07551 0.07104 -0.0555 1.0000 0.0052
-15.750 -0.8301 0.07176 0.06719 -0.0569 1.0000 0.0053
-15.500 -0.8316 0.06834 0.06369 -0.0582 1.0000 0.0052
-15.250 -0.8333 0.06499 0.06026 -0.0593 1.0000 0.0053
-15.000 -0.8342 0.06185 0.05705 -0.0603 1.0000 0.0054
-14.750 -0.8365 0.05864 0.05377 -0.0612 1.0000 0.0054
-14.500 -0.8362 0.05582 0.05088 -0.0619 1.0000 0.0054
-14.250 -0.8376 0.05290 0.04791 -0.0626 1.0000 0.0056
-14.000 -0.8365 0.05035 0.04530 -0.0630 1.0000 0.0056
-13.750 -0.8354 0.04792 0.04282 -0.0634 1.0000 0.0057
-13.500 -0.8351 0.04555 0.04039 -0.0635 1.0000 0.0058
-13.250 -0.8329 0.04345 0.03824 -0.0635 1.0000 0.0058
-13.000 -0.8304 0.04143 0.03617 -0.0633 1.0000 0.0059
-12.750 -0.8285 0.03944 0.03413 -0.0630 1.0000 0.0060
-12.500 -0.8271 0.03748 0.03212 -0.0626 1.0000 0.0061
-12.250 -0.8244 0.03571 0.03031 -0.0620 1.0000 0.0062
-12.000 -0.8235 0.03389 0.02845 -0.0612 1.0000 0.0063
-11.750 -0.8225 0.03219 0.02670 -0.0602 1.0000 0.0064
-11.500 -0.7978 0.03028 0.02473 -0.0637 0.9965 0.0067
-11.250 -0.7815 0.02844 0.02283 -0.0654 0.9874 0.0068
-11.000 -0.7731 0.02679 0.02113 -0.0654 0.9581 0.0069
-10.750 -0.7253 0.02471 0.01894 -0.0733 0.9333 0.0074
-10.250 -0.5813 0.02118 0.01502 -0.0977 0.8623 0.0092
-10.000 -0.5692 0.02001 0.01363 -0.0977 0.8159 0.0099
-9.750 -0.5663 0.01899 0.01244 -0.0959 0.7859 0.0103
-9.500 -0.5603 0.01814 0.01143 -0.0943 0.7623 0.0109
-9.250 -0.5472 0.01749 0.01065 -0.0931 0.7435 0.0118
-9.000 -0.5322 0.01688 0.00995 -0.0920 0.7269 0.0130
-8.750 -0.5141 0.01639 0.00935 -0.0911 0.7115 0.0143
-8.500 -0.4953 0.01590 0.00877 -0.0903 0.6970 0.0163
-8.250 -0.4750 0.01544 0.00824 -0.0897 0.6826 0.0193
-8.000 -0.4535 0.01501 0.00775 -0.0892 0.6695 0.0233
-7.750 -0.4311 0.01459 0.00728 -0.0888 0.6583 0.0282
-7.500 -0.4083 0.01419 0.00683 -0.0884 0.6473 0.0341
-7.250 -0.3845 0.01378 0.00641 -0.0882 0.6372 0.0423
-7.000 -0.3606 0.01338 0.00600 -0.0880 0.6276 0.0535
-6.750 -0.3363 0.01292 0.00558 -0.0880 0.6180 0.0712
-6.500 -0.3120 0.01244 0.00515 -0.0879 0.6089 0.0964
-6.250 -0.2878 0.01180 0.00466 -0.0880 0.5996 0.1379
-6.000 -0.2643 0.01095 0.00405 -0.0882 0.5912 0.2072
-5.750 -0.2400 0.01004 0.00350 -0.0886 0.5830 0.3011
-5.500 -0.2129 0.00979 0.00333 -0.0888 0.5756 0.3460
-5.250 -0.1845 0.00968 0.00323 -0.0889 0.5684 0.3667
-5.000 -0.1563 0.00965 0.00316 -0.0890 0.5612 0.3839
-4.750 -0.1277 0.00963 0.00310 -0.0892 0.5549 0.3980
-4.500 -0.0991 0.00963 0.00304 -0.0893 0.5481 0.4070
-4.250 -0.0708 0.00966 0.00301 -0.0894 0.5416 0.4173
-4.000 -0.0418 0.00973 0.00301 -0.0895 0.5354 0.4293
-3.750 -0.0133 0.00973 0.00299 -0.0896 0.5292 0.4349
-3.500 0.0151 0.00974 0.00293 -0.0897 0.5239 0.4378
-3.250 0.0441 0.00973 0.00286 -0.0899 0.5190 0.4403
-3.000 0.0729 0.00974 0.00280 -0.0901 0.5139 0.4430
-2.750 0.1014 0.00978 0.00274 -0.0902 0.5090 0.4455
-2.500 0.1301 0.00976 0.00270 -0.0903 0.5046 0.4478
-2.250 0.1588 0.00976 0.00267 -0.0905 0.4997 0.4500
-2.000 0.1874 0.00977 0.00265 -0.0906 0.4950 0.4525
-1.750 0.2158 0.00981 0.00263 -0.0907 0.4909 0.4552
-1.500 0.2447 0.00983 0.00262 -0.0909 0.4874 0.4580
-1.250 0.2735 0.00985 0.00260 -0.0911 0.4837 0.4604
-1.000 0.3022 0.00989 0.00259 -0.0912 0.4798 0.4626
-0.750 0.3305 0.00992 0.00260 -0.0913 0.4759 0.4648
-0.500 0.3589 0.00995 0.00262 -0.0914 0.4724 0.4673
-0.250 0.3877 0.00997 0.00264 -0.0916 0.4691 0.4701
0.000 0.4164 0.01001 0.00267 -0.0918 0.4659 0.4729
0.250 0.4449 0.01006 0.00270 -0.0919 0.4627 0.4757
0.500 0.4732 0.01012 0.00273 -0.0920 0.4595 0.4782
0.750 0.5013 0.01020 0.00277 -0.0921 0.4563 0.4804
1.000 0.5300 0.01022 0.00282 -0.0923 0.4535 0.4830
1.250 0.5586 0.01025 0.00288 -0.0924 0.4506 0.4856
1.500 0.5869 0.01031 0.00294 -0.0926 0.4476 0.4886
1.750 0.6151 0.01038 0.00301 -0.0926 0.4445 0.4918
2.000 0.6431 0.01047 0.00308 -0.0927 0.4416 0.4950
2.500 0.6996 0.01059 0.00325 -0.0929 0.4364 0.5004
2.750 0.7278 0.01065 0.00334 -0.0930 0.4334 0.5034
3.000 0.7558 0.01072 0.00344 -0.0931 0.4305 0.5066
3.250 0.7837 0.01081 0.00354 -0.0932 0.4276 0.5099
3.500 0.8112 0.01092 0.00364 -0.0932 0.4248 0.5133
3.750 0.8388 0.01102 0.00376 -0.0932 0.4221 0.5167
4.000 0.8669 0.01107 0.00389 -0.0933 0.4195 0.5205
4.250 0.8947 0.01115 0.00402 -0.0933 0.4164 0.5244
4.500 0.9223 0.01125 0.00415 -0.0933 0.4133 0.5282
4.750 0.9494 0.01136 0.00428 -0.0933 0.4101 0.5319
5.000 0.9761 0.01150 0.00443 -0.0932 0.4068 0.5355
5.250 1.0037 0.01157 0.00458 -0.0932 0.4034 0.5398
5.500 1.0309 0.01165 0.00473 -0.0932 0.3993 0.5447
5.750 1.0576 0.01177 0.00488 -0.0930 0.3948 0.5496
6.000 1.0835 0.01192 0.00505 -0.0928 0.3907 0.5543
6.250 1.1105 0.01201 0.00523 -0.0927 0.3867 0.5595
6.500 1.1371 0.01212 0.00541 -0.0926 0.3820 0.5648
6.750 1.1627 0.01227 0.00558 -0.0923 0.3768 0.5699
7.000 1.1883 0.01241 0.00579 -0.0920 0.3717 0.5758
7.250 1.2141 0.01253 0.00598 -0.0917 0.3651 0.5827
7.500 1.2383 0.01272 0.00620 -0.0912 0.3587 0.5892
7.750 1.2637 0.01286 0.00642 -0.0909 0.3516 0.5964
8.000 1.2870 0.01308 0.00666 -0.0903 0.3433 0.6036
8.250 1.3109 0.01327 0.00692 -0.0897 0.3336 0.6110
8.500 1.3328 0.01354 0.00721 -0.0889 0.3225 0.6194
8.750 1.3534 0.01385 0.00754 -0.0878 0.3097 0.6282
9.000 1.3723 0.01424 0.00792 -0.0865 0.2948 0.6383
9.250 1.3892 0.01468 0.00836 -0.0848 0.2784 0.6483
9.500 1.4027 0.01519 0.00886 -0.0826 0.2612 0.6587
9.750 1.4126 0.01578 0.00942 -0.0798 0.2432 0.6700
10.000 1.4204 0.01650 0.01010 -0.0768 0.2246 0.6817
10.250 1.4255 0.01734 0.01090 -0.0735 0.2062 0.6953
10.500 1.4301 0.01823 0.01178 -0.0704 0.1895 0.7111
10.750 1.4337 0.01917 0.01274 -0.0672 0.1749 0.7293
11.250 1.4375 0.02138 0.01505 -0.0613 0.1497 0.7779
11.500 1.4372 0.02264 0.01642 -0.0585 0.1389 0.8158
12.000 1.4315 0.02582 0.01982 -0.0533 0.1195 1.0000
12.250 1.4296 0.02794 0.02194 -0.0517 0.1095 1.0000
12.500 1.4293 0.03009 0.02411 -0.0505 0.1019 1.0000
12.750 1.4258 0.03265 0.02668 -0.0495 0.0943 1.0000
13.000 1.4235 0.03523 0.02928 -0.0487 0.0872 1.0000
13.250 1.4214 0.03792 0.03201 -0.0481 0.0821 1.0000
13.500 1.4182 0.04080 0.03491 -0.0477 0.0762 1.0000
13.750 1.4142 0.04384 0.03799 -0.0474 0.0710 1.0000
14.000 1.4099 0.04700 0.04119 -0.0472 0.0660 1.0000
14.250 1.4072 0.05010 0.04434 -0.0472 0.0622 1.0000
14.500 1.4034 0.05340 0.04768 -0.0474 0.0579 1.0000
14.750 1.4003 0.05674 0.05106 -0.0476 0.0542 1.0000
15.000 1.3972 0.06014 0.05450 -0.0480 0.0504 1.0000
15.250 1.3942 0.06362 0.05803 -0.0485 0.0471 1.0000
15.500 1.3928 0.06701 0.06147 -0.0491 0.0442 1.0000
15.750 1.3891 0.07074 0.06524 -0.0498 0.0411 1.0000
16.000 1.3879 0.07421 0.06876 -0.0506 0.0382 1.0000
16.250 1.3850 0.07799 0.07259 -0.0515 0.0356 1.0000
16.500 1.3838 0.08162 0.07627 -0.0525 0.0331 1.0000
17.000 1.3802 0.08917 0.08393 -0.0546 0.0286 1.0000
17.250 1.3779 0.09311 0.08791 -0.0559 0.0265 1.0000
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