EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 552 AIRFOIL (e552-il) Reynolds number: 500,000 Max Cl/Cd: 100.49 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e552-il-500000-n5.txt Download as CSV file: xf-e552-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.6824 0.13818 0.13510 -0.0265 1.0000 0.0049
-18.250 -0.7024 0.12935 0.12614 -0.0310 1.0000 0.0049
-18.000 -0.7242 0.12052 0.11717 -0.0354 1.0000 0.0049
-17.750 -0.7396 0.11331 0.10985 -0.0390 1.0000 0.0048
-17.500 -0.7563 0.10593 0.10231 -0.0428 1.0000 0.0049
-17.250 -0.7693 0.09959 0.09586 -0.0459 1.0000 0.0048
-17.000 -0.7813 0.09362 0.08977 -0.0489 1.0000 0.0048
-16.750 -0.7902 0.08836 0.08439 -0.0514 1.0000 0.0048
-16.500 -0.7991 0.08324 0.07915 -0.0538 1.0000 0.0049
-16.250 -0.8051 0.07878 0.07459 -0.0558 1.0000 0.0049
-16.000 -0.8100 0.07460 0.07030 -0.0576 1.0000 0.0049
-15.750 -0.8144 0.07063 0.06622 -0.0592 1.0000 0.0049
-15.500 -0.8174 0.06699 0.06250 -0.0606 1.0000 0.0049
-15.250 -0.8194 0.06357 0.05898 -0.0618 1.0000 0.0050
-15.000 -0.8205 0.06040 0.05572 -0.0628 1.0000 0.0050
-14.750 -0.8210 0.05739 0.05263 -0.0636 1.0000 0.0050
-14.500 -0.8200 0.05465 0.04980 -0.0643 1.0000 0.0050
-14.250 -0.8191 0.05200 0.04707 -0.0648 1.0000 0.0050
-14.000 -0.8188 0.04939 0.04440 -0.0652 1.0000 0.0051
-13.750 -0.8200 0.04677 0.04171 -0.0654 1.0000 0.0052
-13.500 -0.8202 0.04438 0.03925 -0.0655 1.0000 0.0053
-13.250 -0.8178 0.04231 0.03712 -0.0654 1.0000 0.0052
-13.000 -0.8159 0.04026 0.03502 -0.0652 1.0000 0.0054
-12.750 -0.8131 0.03834 0.03306 -0.0648 1.0000 0.0054
-12.500 -0.8111 0.03643 0.03110 -0.0644 1.0000 0.0055
-12.250 -0.8026 0.03465 0.02927 -0.0647 0.9993 0.0056
-12.000 -0.7892 0.03285 0.02743 -0.0656 0.9868 0.0058
-11.750 -0.7343 0.03036 0.02482 -0.0757 0.9311 0.0061
-11.500 -0.6398 0.02785 0.02202 -0.0935 0.8847 0.0067
-11.250 -0.6138 0.02670 0.02054 -0.0962 0.8217 0.0069
-11.000 -0.6063 0.02559 0.01922 -0.0952 0.7873 0.0071
-10.750 -0.6008 0.02436 0.01784 -0.0941 0.7617 0.0072
-10.500 -0.5951 0.02311 0.01647 -0.0930 0.7414 0.0075
-10.250 -0.5877 0.02199 0.01524 -0.0919 0.7247 0.0077
-10.000 -0.5804 0.02089 0.01403 -0.0907 0.7101 0.0080
-9.750 -0.5730 0.01989 0.01293 -0.0893 0.6971 0.0084
-9.500 -0.5695 0.01896 0.01189 -0.0872 0.6851 0.0087
-9.250 -0.5606 0.01825 0.01108 -0.0855 0.6739 0.0092
-9.000 -0.5467 0.01763 0.01037 -0.0843 0.6636 0.0096
-8.500 -0.5126 0.01655 0.00913 -0.0822 0.6434 0.0115
-8.250 -0.4935 0.01605 0.00856 -0.0814 0.6348 0.0131
-8.000 -0.4726 0.01562 0.00807 -0.0808 0.6262 0.0149
-7.750 -0.4512 0.01519 0.00759 -0.0803 0.6188 0.0180
-7.500 -0.4287 0.01478 0.00715 -0.0798 0.6114 0.0221
-7.250 -0.4059 0.01439 0.00673 -0.0794 0.6046 0.0276
-7.000 -0.3822 0.01399 0.00633 -0.0792 0.5980 0.0351
-6.750 -0.3586 0.01359 0.00593 -0.0789 0.5915 0.0457
-6.500 -0.3346 0.01316 0.00554 -0.0787 0.5855 0.0619
-6.250 -0.3105 0.01269 0.00514 -0.0786 0.5793 0.0858
-5.750 -0.2628 0.01149 0.00425 -0.0785 0.5683 0.1729
-5.500 -0.2404 0.01049 0.00362 -0.0786 0.5633 0.2664
-5.250 -0.2161 0.00980 0.00328 -0.0787 0.5586 0.3627
-5.000 -0.1881 0.00969 0.00320 -0.0789 0.5543 0.3922
-4.750 -0.1595 0.00965 0.00314 -0.0790 0.5499 0.4101
-4.500 -0.1310 0.00966 0.00310 -0.0792 0.5455 0.4248
-4.000 -0.0736 0.00970 0.00303 -0.0795 0.5374 0.4441
-3.750 -0.0449 0.00975 0.00306 -0.0796 0.5333 0.4561
-3.500 -0.0160 0.00983 0.00303 -0.0798 0.5295 0.4639
-3.250 0.0125 0.00981 0.00297 -0.0800 0.5262 0.4661
-3.000 0.0413 0.00980 0.00291 -0.0802 0.5232 0.4681
-2.750 0.0702 0.00978 0.00286 -0.0804 0.5201 0.4700
-2.500 0.0990 0.00978 0.00281 -0.0806 0.5169 0.4719
-2.250 0.1278 0.00979 0.00277 -0.0808 0.5139 0.4742
-2.000 0.1564 0.00982 0.00273 -0.0809 0.5109 0.4764
-1.750 0.1852 0.00984 0.00269 -0.0812 0.5081 0.4783
-1.500 0.2142 0.00984 0.00266 -0.0814 0.5053 0.4800
-1.250 0.2430 0.00983 0.00265 -0.0816 0.5026 0.4818
-1.000 0.2716 0.00984 0.00265 -0.0818 0.5000 0.4837
-0.750 0.3003 0.00986 0.00265 -0.0820 0.4976 0.4858
-0.500 0.3288 0.00991 0.00266 -0.0822 0.4952 0.4882
-0.250 0.3574 0.00995 0.00268 -0.0824 0.4929 0.4905
0.000 0.3863 0.00997 0.00269 -0.0826 0.4905 0.4926
0.250 0.4152 0.01000 0.00271 -0.0828 0.4880 0.4946
0.500 0.4438 0.01003 0.00274 -0.0830 0.4857 0.4966
0.750 0.4723 0.01006 0.00278 -0.0832 0.4835 0.4986
1.000 0.5007 0.01010 0.00282 -0.0834 0.4813 0.5009
1.250 0.5290 0.01017 0.00287 -0.0835 0.4790 0.5035
1.500 0.5575 0.01023 0.00294 -0.0837 0.4769 0.5063
1.750 0.5862 0.01027 0.00300 -0.0840 0.4749 0.5090
2.000 0.6148 0.01032 0.00306 -0.0842 0.4726 0.5114
2.250 0.6432 0.01036 0.00313 -0.0843 0.4701 0.5137
2.500 0.6714 0.01041 0.00321 -0.0845 0.4678 0.5162
2.750 0.6995 0.01048 0.00329 -0.0846 0.4656 0.5190
3.000 0.7274 0.01057 0.00339 -0.0847 0.4633 0.5220
3.250 0.7556 0.01065 0.00349 -0.0849 0.4611 0.5251
3.750 0.8120 0.01075 0.00370 -0.0852 0.4559 0.5315
4.000 0.8397 0.01082 0.00380 -0.0853 0.4528 0.5350
4.250 0.8673 0.01090 0.00391 -0.0853 0.4498 0.5386
4.500 0.8945 0.01102 0.00402 -0.0853 0.4467 0.5422
4.750 0.9224 0.01107 0.00415 -0.0855 0.4436 0.5456
5.000 0.9500 0.01113 0.00429 -0.0855 0.4402 0.5494
5.250 0.9772 0.01122 0.00442 -0.0855 0.4366 0.5536
5.500 1.0039 0.01133 0.00454 -0.0854 0.4327 0.5579
5.750 1.0310 0.01141 0.00469 -0.0854 0.4286 0.5624
6.000 1.0580 0.01148 0.00485 -0.0854 0.4240 0.5674
6.250 1.0843 0.01159 0.00500 -0.0852 0.4194 0.5729
6.500 1.1104 0.01171 0.00516 -0.0851 0.4150 0.5781
6.750 1.1370 0.01179 0.00534 -0.0850 0.4094 0.5835
7.000 1.1623 0.01192 0.00551 -0.0846 0.4030 0.5895
7.250 1.1880 0.01204 0.00569 -0.0844 0.3963 0.5953
7.500 1.2124 0.01219 0.00589 -0.0840 0.3878 0.6018
7.750 1.2370 0.01234 0.00610 -0.0836 0.3783 0.6088
8.000 1.2601 0.01254 0.00634 -0.0829 0.3674 0.6163
8.250 1.2819 0.01280 0.00662 -0.0820 0.3541 0.6246
8.500 1.3017 0.01313 0.00695 -0.0809 0.3365 0.6330
8.750 1.3189 0.01357 0.00735 -0.0793 0.3167 0.6418
9.000 1.3327 0.01413 0.00786 -0.0772 0.2951 0.6508
9.250 1.3427 0.01475 0.00842 -0.0745 0.2729 0.6603
9.500 1.3483 0.01545 0.00907 -0.0710 0.2526 0.6707
9.750 1.3545 0.01619 0.00979 -0.0678 0.2337 0.6819
10.000 1.3583 0.01705 0.01062 -0.0644 0.2149 0.6944
10.250 1.3613 0.01797 0.01153 -0.0612 0.1985 0.7093
10.500 1.3624 0.01903 0.01260 -0.0579 0.1831 0.7262
10.750 1.3636 0.02016 0.01378 -0.0550 0.1702 0.7459
11.000 1.3641 0.02145 0.01512 -0.0523 0.1588 0.7702
11.750 1.3629 0.02609 0.02018 -0.0459 0.1298 1.0000
12.000 1.3629 0.02817 0.02226 -0.0446 0.1215 1.0000
12.250 1.3609 0.03051 0.02460 -0.0435 0.1124 1.0000
12.500 1.3604 0.03284 0.02694 -0.0426 0.1041 1.0000
12.750 1.3575 0.03546 0.02956 -0.0418 0.0964 1.0000
13.000 1.3570 0.03793 0.03205 -0.0412 0.0898 1.0000
13.250 1.3532 0.04076 0.03489 -0.0406 0.0821 1.0000
13.500 1.3499 0.04362 0.03775 -0.0402 0.0756 1.0000
13.750 1.3473 0.04649 0.04064 -0.0399 0.0684 1.0000
14.000 1.3443 0.04950 0.04365 -0.0397 0.0628 1.0000
14.250 1.3429 0.05243 0.04659 -0.0397 0.0566 1.0000
14.500 1.3417 0.05540 0.04959 -0.0397 0.0520 1.0000
14.750 1.3431 0.05816 0.05238 -0.0399 0.0483 1.0000
15.000 1.3423 0.06124 0.05548 -0.0402 0.0447 1.0000
15.250 1.3442 0.06407 0.05836 -0.0405 0.0417 1.0000
15.500 1.3444 0.06714 0.06146 -0.0409 0.0383 1.0000
15.750 1.3446 0.07028 0.06464 -0.0414 0.0357 1.0000
16.000 1.3470 0.07318 0.06760 -0.0419 0.0333 1.0000
16.250 1.3467 0.07651 0.07098 -0.0426 0.0308 1.0000
16.500 1.3471 0.07976 0.07427 -0.0433 0.0283 1.0000
16.750 1.3475 0.08308 0.07763 -0.0441 0.0260 1.0000
17.250 1.3485 0.08986 0.08453 -0.0460 0.0229 1.0000
17.500 1.3483 0.09341 0.08811 -0.0470 0.0207 1.0000
17.750 1.3483 0.09696 0.09173 -0.0482 0.0198 1.0000
18.000 1.3482 0.10059 0.09542 -0.0494 0.0183 1.0000
18.250 1.3480 0.10426 0.09915 -0.0507 0.0168 1.0000
18.500 1.3456 0.10833 0.10326 -0.0522 0.0154 1.0000
18.750 1.3459 0.11199 0.10701 -0.0536 0.0144 1.0000
19.000 1.3451 0.11587 0.11097 -0.0551 0.0135 1.0000
19.250 1.3440 0.11980 0.11496 -0.0568 0.0125 1.0000
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