EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 552 AIRFOIL (e552-il) Reynolds number: 200,000 Max Cl/Cd: 70.74 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e552-il-200000-n5.txt Download as CSV file: xf-e552-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 552 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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6122 0.09981 0.09546 -0.0508 1.0000 0.0104
-15.250 -0.6432 0.08983 0.08522 -0.0563 1.0000 0.0103
-15.000 -0.6625 0.08277 0.07796 -0.0601 1.0000 0.0102
-14.750 -0.6775 0.07689 0.07189 -0.0630 1.0000 0.0102
-14.500 -0.6885 0.07194 0.06678 -0.0652 1.0000 0.0102
-14.250 -0.6969 0.06760 0.06229 -0.0669 1.0000 0.0103
-14.000 -0.7039 0.06365 0.05818 -0.0683 1.0000 0.0104
-13.750 -0.7086 0.06019 0.05457 -0.0692 1.0000 0.0105
-13.500 -0.7118 0.05707 0.05132 -0.0698 1.0000 0.0106
-13.250 -0.7127 0.05431 0.04843 -0.0702 1.0000 0.0106
-13.000 -0.7122 0.05178 0.04578 -0.0703 1.0000 0.0107
-12.750 -0.7102 0.04946 0.04336 -0.0701 1.0000 0.0108
-12.500 -0.7077 0.04728 0.04106 -0.0698 1.0000 0.0110
-12.250 -0.7037 0.04531 0.03901 -0.0693 1.0000 0.0112
-12.000 -0.6992 0.04347 0.03705 -0.0687 1.0000 0.0114
-11.750 -0.6944 0.04173 0.03522 -0.0678 1.0000 0.0117
-11.500 -0.6893 0.04011 0.03352 -0.0669 1.0000 0.0119
-11.250 -0.6846 0.03856 0.03193 -0.0658 1.0000 0.0121
-11.000 -0.6822 0.03695 0.03032 -0.0646 1.0000 0.0124
-10.750 -0.6754 0.03540 0.02876 -0.0641 0.9987 0.0126
-10.500 -0.6559 0.03347 0.02680 -0.0660 0.9625 0.0131
-10.250 -0.6123 0.03131 0.02450 -0.0730 0.9255 0.0139
-10.000 -0.5614 0.02906 0.02201 -0.0816 0.8902 0.0155
-9.750 -0.5209 0.02736 0.02014 -0.0876 0.8524 0.0174
-9.500 -0.4977 0.02601 0.01857 -0.0897 0.8197 0.0191
-9.250 -0.4866 0.02465 0.01708 -0.0897 0.7934 0.0207
-9.000 -0.4781 0.02352 0.01577 -0.0888 0.7716 0.0221
-8.750 -0.4745 0.02241 0.01451 -0.0871 0.7534 0.0240
-8.500 -0.4686 0.02149 0.01349 -0.0854 0.7376 0.0263
-8.250 -0.4580 0.02067 0.01257 -0.0840 0.7238 0.0303
-8.000 -0.4443 0.01995 0.01176 -0.0828 0.7118 0.0356
-7.750 -0.4294 0.01924 0.01098 -0.0817 0.7008 0.0431
-7.500 -0.4134 0.01851 0.01023 -0.0807 0.6901 0.0536
-7.250 -0.3961 0.01780 0.00953 -0.0799 0.6805 0.0699
-7.000 -0.3781 0.01707 0.00885 -0.0792 0.6711 0.0940
-6.750 -0.3598 0.01624 0.00815 -0.0787 0.6621 0.1312
-6.500 -0.3424 0.01521 0.00735 -0.0782 0.6540 0.1930
-6.250 -0.3260 0.01391 0.00657 -0.0778 0.6462 0.3035
-6.000 -0.3021 0.01368 0.00657 -0.0775 0.6390 0.3851
-5.750 -0.2749 0.01371 0.00653 -0.0774 0.6321 0.4131
-5.500 -0.2473 0.01378 0.00643 -0.0773 0.6254 0.4324
-5.250 -0.2197 0.01390 0.00641 -0.0773 0.6196 0.4474
-5.000 -0.1919 0.01401 0.00647 -0.0771 0.6130 0.4580
-4.750 -0.1642 0.01411 0.00644 -0.0770 0.6072 0.4676
-4.500 -0.1365 0.01433 0.00654 -0.0769 0.6017 0.4811
-4.250 -0.1087 0.01456 0.00674 -0.0767 0.5960 0.4912
-4.000 -0.0807 0.01452 0.00651 -0.0768 0.5914 0.4959
-3.750 -0.0526 0.01447 0.00638 -0.0769 0.5871 0.4980
-3.500 -0.0243 0.01442 0.00627 -0.0770 0.5823 0.5003
-3.250 0.0039 0.01439 0.00615 -0.0771 0.5779 0.5029
-3.000 0.0321 0.01436 0.00598 -0.0773 0.5740 0.5054
-2.750 0.0605 0.01431 0.00584 -0.0775 0.5698 0.5080
-2.500 0.0889 0.01426 0.00569 -0.0778 0.5654 0.5109
-2.250 0.1172 0.01424 0.00559 -0.0779 0.5616 0.5131
-2.000 0.1455 0.01423 0.00552 -0.0780 0.5585 0.5150
-1.750 0.1738 0.01423 0.00546 -0.0782 0.5553 0.5170
-1.500 0.2022 0.01422 0.00543 -0.0784 0.5518 0.5193
-1.250 0.2306 0.01422 0.00539 -0.0786 0.5483 0.5220
-1.000 0.2590 0.01424 0.00533 -0.0788 0.5450 0.5249
-0.750 0.2877 0.01428 0.00525 -0.0791 0.5421 0.5277
-0.500 0.3159 0.01429 0.00527 -0.0792 0.5391 0.5297
-0.250 0.3440 0.01431 0.00531 -0.0794 0.5360 0.5318
0.000 0.3722 0.01435 0.00534 -0.0796 0.5330 0.5342
0.250 0.4005 0.01439 0.00537 -0.0797 0.5303 0.5368
0.500 0.4289 0.01445 0.00538 -0.0800 0.5277 0.5400
0.750 0.4577 0.01454 0.00539 -0.0803 0.5252 0.5432
1.000 0.4854 0.01458 0.00549 -0.0804 0.5222 0.5459
1.250 0.5133 0.01464 0.00559 -0.0805 0.5194 0.5484
1.500 0.5413 0.01471 0.00570 -0.0806 0.5167 0.5512
1.750 0.5694 0.01479 0.00578 -0.0808 0.5141 0.5542
2.000 0.5977 0.01488 0.00584 -0.0810 0.5116 0.5576
2.250 0.6264 0.01500 0.00592 -0.0813 0.5094 0.5611
2.500 0.6535 0.01508 0.00612 -0.0813 0.5067 0.5641
2.750 0.6809 0.01518 0.00629 -0.0813 0.5038 0.5677
3.000 0.7085 0.01529 0.00644 -0.0814 0.5009 0.5716
3.250 0.7363 0.01540 0.00657 -0.0816 0.4983 0.5757
3.500 0.7642 0.01551 0.00671 -0.0817 0.4959 0.5791
3.750 0.7924 0.01565 0.00687 -0.0819 0.4937 0.5827
4.000 0.8187 0.01578 0.00712 -0.0818 0.4906 0.5870
4.250 0.8455 0.01592 0.00733 -0.0818 0.4874 0.5918
4.500 0.8723 0.01603 0.00754 -0.0818 0.4843 0.5962
4.750 0.8995 0.01615 0.00772 -0.0818 0.4813 0.6011
5.000 0.9273 0.01628 0.00786 -0.0819 0.4786 0.6068
5.250 0.9528 0.01643 0.00814 -0.0817 0.4748 0.6119
5.500 0.9783 0.01656 0.00840 -0.0814 0.4708 0.6172
5.750 1.0045 0.01668 0.00860 -0.0812 0.4670 0.6233
6.000 1.0314 0.01679 0.00876 -0.0812 0.4637 0.6291
6.250 1.0565 0.01695 0.00904 -0.0809 0.4597 0.6358
6.500 1.0808 0.01709 0.00932 -0.0804 0.4547 0.6433
6.750 1.1058 0.01718 0.00952 -0.0800 0.4501 0.6508
7.000 1.1313 0.01730 0.00969 -0.0797 0.4458 0.6594
7.250 1.1537 0.01745 0.01004 -0.0790 0.4400 0.6678
7.500 1.1776 0.01756 0.01026 -0.0784 0.4347 0.6770
7.750 1.2011 0.01769 0.01049 -0.0778 0.4294 0.6870
8.000 1.2225 0.01784 0.01082 -0.0768 0.4224 0.6977
8.250 1.2452 0.01793 0.01098 -0.0760 0.4163 0.7101
8.500 1.2647 0.01813 0.01139 -0.0748 0.4079 0.7238
9.000 1.3025 0.01845 0.01198 -0.0720 0.3903 0.7558
9.250 1.3193 0.01865 0.01232 -0.0703 0.3802 0.7750
9.500 1.3336 0.01887 0.01266 -0.0681 0.3688 0.7987
9.750 1.3428 0.01911 0.01302 -0.0650 0.3561 0.8313
10.000 1.3461 0.01934 0.01341 -0.0608 0.3424 0.9025
10.250 1.3532 0.01989 0.01396 -0.0580 0.3258 1.0000
10.500 1.3571 0.02073 0.01475 -0.0550 0.3078 1.0000
10.750 1.3573 0.02184 0.01579 -0.0519 0.2898 1.0000
11.000 1.3549 0.02323 0.01713 -0.0490 0.2727 1.0000
11.250 1.3502 0.02495 0.01880 -0.0463 0.2562 1.0000
11.500 1.3452 0.02693 0.02075 -0.0441 0.2410 1.0000
11.750 1.3392 0.02921 0.02300 -0.0423 0.2261 1.0000
12.000 1.3339 0.03164 0.02541 -0.0408 0.2126 1.0000
12.250 1.3281 0.03427 0.02803 -0.0397 0.1995 1.0000
12.500 1.3222 0.03706 0.03081 -0.0388 0.1872 1.0000
12.750 1.3162 0.03997 0.03371 -0.0381 0.1759 1.0000
13.000 1.3097 0.04303 0.03676 -0.0375 0.1654 1.0000
13.250 1.3054 0.04597 0.03972 -0.0371 0.1548 1.0000
13.500 1.3014 0.04898 0.04274 -0.0369 0.1449 1.0000
13.750 1.2970 0.05215 0.04590 -0.0368 0.1364 1.0000
14.000 1.2942 0.05523 0.04901 -0.0369 0.1273 1.0000
14.250 1.2921 0.05833 0.05214 -0.0370 0.1191 1.0000
14.750 1.2881 0.06476 0.05861 -0.0377 0.1038 1.0000
15.000 1.2853 0.06818 0.06205 -0.0382 0.0972 1.0000
15.250 1.2851 0.07135 0.06526 -0.0387 0.0903 1.0000
15.500 1.2829 0.07486 0.06879 -0.0394 0.0844 1.0000
15.750 1.2824 0.07819 0.07217 -0.0400 0.0780 1.0000
16.000 1.2801 0.08182 0.07583 -0.0409 0.0729 1.0000
16.250 1.2799 0.08525 0.07930 -0.0417 0.0673 1.0000
16.500 1.2767 0.08914 0.08321 -0.0428 0.0627 1.0000
16.750 1.2772 0.09257 0.08671 -0.0438 0.0580 1.0000
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Polar data table (+)
Polar graphs
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