EPPLER 554 AIRFOIL (e554-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 554 AIRFOIL (e554-il) Reynolds number: 500,000 Max Cl/Cd: 103.16 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e554-il-500000.txt Download as CSV file: xf-e554-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.2970 0.16707 0.16480 -0.0248 1.0000 0.0186
-17.500 -0.6313 0.13346 0.13063 -0.0306 1.0000 0.0094
-17.250 -0.6791 0.11784 0.11474 -0.0392 1.0000 0.0094
-17.000 -0.6740 0.11502 0.11193 -0.0403 1.0000 0.0091
-16.750 -0.7079 0.10371 0.10037 -0.0468 1.0000 0.0092
-16.500 -0.7200 0.09786 0.09444 -0.0495 1.0000 0.0090
-16.250 -0.7388 0.09067 0.08709 -0.0534 1.0000 0.0091
-16.000 -0.7539 0.08449 0.08075 -0.0565 1.0000 0.0090
-15.750 -0.7688 0.07862 0.07471 -0.0594 1.0000 0.0091
-15.500 -0.7760 0.07421 0.07018 -0.0613 1.0000 0.0090
-15.250 -0.7888 0.06907 0.06484 -0.0636 1.0000 0.0091
-15.000 -0.7942 0.06520 0.06084 -0.0651 1.0000 0.0091
-14.750 -0.7981 0.06172 0.05725 -0.0661 1.0000 0.0091
-14.500 -0.8020 0.05830 0.05368 -0.0674 1.0000 0.0092
-14.000 -0.8053 0.05246 0.04758 -0.0687 1.0000 0.0093
-13.750 -0.8051 0.04997 0.04500 -0.0681 1.0000 0.0095
-13.500 -0.8023 0.04786 0.04284 -0.0676 1.0000 0.0096
-13.250 -0.7984 0.04593 0.04087 -0.0674 1.0000 0.0097
-13.000 -0.7938 0.04408 0.03897 -0.0671 1.0000 0.0098
-12.750 -0.7896 0.04225 0.03710 -0.0666 1.0000 0.0099
-12.500 -0.7851 0.04052 0.03533 -0.0661 1.0000 0.0101
-12.250 -0.7803 0.03887 0.03363 -0.0655 1.0000 0.0102
-12.000 -0.7762 0.03724 0.03196 -0.0646 1.0000 0.0104
-11.750 -0.7723 0.03565 0.03032 -0.0637 1.0000 0.0106
-11.500 -0.7684 0.03416 0.02879 -0.0626 1.0000 0.0108
-11.250 -0.7661 0.03267 0.02727 -0.0612 1.0000 0.0109
-11.000 -0.7648 0.03122 0.02578 -0.0596 1.0000 0.0111
-10.750 -0.7654 0.02982 0.02434 -0.0577 1.0000 0.0113
-10.500 -0.7684 0.02850 0.02298 -0.0554 0.9999 0.0115
-10.250 -0.7381 0.02639 0.02082 -0.0601 0.9947 0.0118
-10.000 -0.7128 0.02422 0.01863 -0.0643 0.9843 0.0124
-9.750 -0.6956 0.02248 0.01685 -0.0660 0.9615 0.0129
-9.500 -0.6609 0.02077 0.01505 -0.0706 0.9452 0.0138
-9.250 -0.6154 0.01892 0.01313 -0.0775 0.9299 0.0152
-9.000 -0.5553 0.01747 0.01157 -0.0864 0.9135 0.0177
-8.750 -0.5033 0.01630 0.01025 -0.0932 0.8821 0.0206
-8.500 -0.4776 0.01548 0.00925 -0.0943 0.8455 0.0245
-8.250 -0.4597 0.01480 0.00846 -0.0936 0.8156 0.0300
-7.250 -0.3799 0.01245 0.00604 -0.0909 0.7365 0.0968
-7.000 -0.3583 0.01173 0.00545 -0.0906 0.7213 0.1386
-6.750 -0.3378 0.01068 0.00469 -0.0905 0.7071 0.2156
-6.500 -0.3162 0.00965 0.00409 -0.0906 0.6938 0.3297
-6.250 -0.2896 0.00951 0.00399 -0.0906 0.6808 0.3728
-6.000 -0.2618 0.00953 0.00393 -0.0905 0.6682 0.3947
-5.750 -0.2338 0.00958 0.00391 -0.0905 0.6570 0.4079
-5.250 -0.1774 0.00971 0.00383 -0.0905 0.6360 0.4256
-5.000 -0.1493 0.00979 0.00382 -0.0905 0.6266 0.4338
-4.750 -0.1208 0.00991 0.00386 -0.0905 0.6171 0.4419
-4.500 -0.0925 0.00997 0.00380 -0.0905 0.6084 0.4476
-4.250 -0.0643 0.01006 0.00387 -0.0905 0.5995 0.4542
-4.000 -0.0357 0.01032 0.00398 -0.0905 0.5916 0.4629
-3.750 -0.0075 0.01029 0.00397 -0.0905 0.5838 0.4682
-3.500 0.0207 0.01032 0.00391 -0.0905 0.5769 0.4709
-3.250 0.0495 0.01031 0.00385 -0.0907 0.5702 0.4739
-3.000 0.0781 0.01032 0.00378 -0.0908 0.5636 0.4767
-2.750 0.1067 0.01037 0.00371 -0.0910 0.5576 0.4791
-2.500 0.1354 0.01029 0.00361 -0.0911 0.5515 0.4818
-2.250 0.1637 0.01028 0.00355 -0.0912 0.5456 0.4844
-2.000 0.1921 0.01031 0.00354 -0.0913 0.5404 0.4869
-1.750 0.2210 0.01030 0.00352 -0.0915 0.5355 0.4895
-1.500 0.2496 0.01033 0.00349 -0.0917 0.5306 0.4923
-1.250 0.2782 0.01041 0.00348 -0.0918 0.5259 0.4952
-1.000 0.3071 0.01046 0.00347 -0.0920 0.5215 0.4976
-0.750 0.3356 0.01038 0.00343 -0.0922 0.5170 0.5005
-0.500 0.3641 0.01040 0.00343 -0.0923 0.5128 0.5031
-0.250 0.3925 0.01048 0.00346 -0.0925 0.5088 0.5058
0.000 0.4213 0.01054 0.00350 -0.0926 0.5052 0.5088
0.250 0.4500 0.01057 0.00353 -0.0928 0.5015 0.5120
0.500 0.4788 0.01063 0.00356 -0.0930 0.4977 0.5148
0.750 0.5071 0.01063 0.00356 -0.0932 0.4941 0.5178
1.000 0.5355 0.01075 0.00364 -0.0933 0.4906 0.5207
1.250 0.5641 0.01078 0.00371 -0.0935 0.4876 0.5238
1.500 0.5926 0.01082 0.00377 -0.0936 0.4843 0.5270
1.750 0.6211 0.01088 0.00382 -0.0938 0.4809 0.5303
2.000 0.6496 0.01096 0.00388 -0.0940 0.4778 0.5335
2.250 0.6778 0.01105 0.00398 -0.0941 0.4745 0.5372
2.500 0.7062 0.01114 0.00410 -0.0943 0.4715 0.5407
2.750 0.7344 0.01119 0.00419 -0.0944 0.4686 0.5444
3.000 0.7627 0.01126 0.00429 -0.0945 0.4655 0.5481
3.250 0.7909 0.01133 0.00436 -0.0946 0.4624 0.5516
3.500 0.8189 0.01141 0.00447 -0.0947 0.4594 0.5555
3.750 0.8473 0.01161 0.00466 -0.0949 0.4561 0.5596
4.000 0.8750 0.01166 0.00478 -0.0950 0.4535 0.5642
4.250 0.9029 0.01174 0.00490 -0.0950 0.4503 0.5686
4.500 0.9304 0.01178 0.00502 -0.0950 0.4471 0.5732
4.750 0.9580 0.01187 0.00514 -0.0951 0.4439 0.5779
5.000 0.9860 0.01207 0.00532 -0.0952 0.4404 0.5830
5.250 1.0131 0.01215 0.00547 -0.0952 0.4371 0.5880
5.500 1.0399 0.01218 0.00561 -0.0950 0.4333 0.5934
5.750 1.0668 0.01226 0.00573 -0.0949 0.4294 0.5996
6.000 1.0938 0.01238 0.00587 -0.0949 0.4256 0.6059
6.250 1.1208 0.01254 0.00609 -0.0948 0.4218 0.6123
6.500 1.1469 0.01259 0.00624 -0.0946 0.4178 0.6195
6.750 1.1730 0.01265 0.00638 -0.0943 0.4134 0.6265
7.000 1.1990 0.01276 0.00653 -0.0941 0.4089 0.6345
7.250 1.2247 0.01290 0.00674 -0.0938 0.4043 0.6430
7.500 1.2500 0.01295 0.00691 -0.0934 0.3993 0.6526
7.750 1.2750 0.01303 0.00707 -0.0930 0.3942 0.6625
8.000 1.2997 0.01320 0.00728 -0.0926 0.3889 0.6737
8.250 1.3242 0.01324 0.00747 -0.0921 0.3827 0.6853
8.500 1.3476 0.01337 0.00766 -0.0914 0.3763 0.6981
8.750 1.3713 0.01348 0.00789 -0.0908 0.3695 0.7129
9.000 1.3938 0.01360 0.00811 -0.0899 0.3615 0.7299
9.250 1.4160 0.01375 0.00837 -0.0890 0.3533 0.7491
9.500 1.4358 0.01394 0.00864 -0.0878 0.3435 0.7716
9.750 1.4556 0.01411 0.00894 -0.0864 0.3320 0.7987
10.000 1.4712 0.01433 0.00928 -0.0844 0.3188 0.8362
10.250 1.4765 0.01440 0.00954 -0.0801 0.3059 1.0000
10.500 1.4888 0.01492 0.01000 -0.0777 0.2896 1.0000
10.750 1.4983 0.01556 0.01058 -0.0750 0.2720 1.0000
11.000 1.5047 0.01637 0.01130 -0.0720 0.2536 1.0000
11.250 1.5075 0.01734 0.01220 -0.0687 0.2354 1.0000
11.500 1.5095 0.01842 0.01322 -0.0655 0.2170 1.0000
11.750 1.5093 0.01969 0.01443 -0.0623 0.2005 1.0000
12.000 1.5077 0.02115 0.01584 -0.0593 0.1859 1.0000
12.250 1.5046 0.02286 0.01752 -0.0566 0.1723 1.0000
12.500 1.5004 0.02484 0.01947 -0.0543 0.1601 1.0000
12.750 1.4965 0.02700 0.02163 -0.0524 0.1490 1.0000
13.000 1.4930 0.02933 0.02397 -0.0510 0.1383 1.0000
13.250 1.4879 0.03196 0.02661 -0.0497 0.1291 1.0000
13.500 1.4799 0.03501 0.02966 -0.0487 0.1203 1.0000
13.750 1.4748 0.03795 0.03262 -0.0480 0.1116 1.0000
14.000 1.4680 0.04115 0.03584 -0.0475 0.1044 1.0000
14.250 1.4598 0.04462 0.03933 -0.0472 0.0975 1.0000
14.500 1.4542 0.04793 0.04268 -0.0471 0.0912 1.0000
14.750 1.4451 0.05173 0.04649 -0.0471 0.0851 1.0000
15.000 1.4406 0.05516 0.04997 -0.0473 0.0794 1.0000
15.250 1.4316 0.05921 0.05403 -0.0477 0.0739 1.0000
15.500 1.4282 0.06270 0.05757 -0.0482 0.0690 1.0000
15.750 1.4202 0.06687 0.06176 -0.0489 0.0642 1.0000
16.000 1.4169 0.07053 0.06548 -0.0496 0.0595 1.0000
16.250 1.4101 0.07473 0.06970 -0.0505 0.0552 1.0000
16.500 1.4070 0.07853 0.07354 -0.0514 0.0511 1.0000
16.750 1.4009 0.08282 0.07786 -0.0526 0.0476 1.0000
17.000 1.3981 0.08672 0.08181 -0.0537 0.0441 1.0000
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Polar data table (+)
Polar graphs
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