EPPLER 553 AIRFOIL (e553-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 553 AIRFOIL (e553-il) Reynolds number: 200,000 Max Cl/Cd: 71.79 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e553-il-200000.txt Download as CSV file: xf-e553-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 553 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.5763 0.09018 0.08586 -0.0727 1.0000 0.0224
-14.250 -0.5985 0.08362 0.07918 -0.0760 1.0000 0.0223
-14.000 -0.6101 0.07885 0.07435 -0.0777 1.0000 0.0221
-13.750 -0.6312 0.07339 0.06874 -0.0800 1.0000 0.0221
-13.500 -0.6454 0.06894 0.06419 -0.0814 1.0000 0.0218
-13.250 -0.6592 0.06483 0.05995 -0.0824 1.0000 0.0217
-13.000 -0.6746 0.06086 0.05583 -0.0833 1.0000 0.0216
-12.750 -0.6905 0.05709 0.05189 -0.0836 1.0000 0.0215
-12.500 -0.7003 0.05399 0.04867 -0.0833 1.0000 0.0213
-12.250 -0.7141 0.05091 0.04541 -0.0825 1.0000 0.0213
-12.000 -0.7254 0.04827 0.04262 -0.0811 1.0000 0.0213
-11.750 -0.7347 0.04614 0.04037 -0.0791 1.0000 0.0212
-11.500 -0.7484 0.04442 0.03855 -0.0760 1.0000 0.0212
-11.250 -0.7729 0.04349 0.03755 -0.0712 1.0000 0.0215
-11.000 -0.7956 0.04283 0.03688 -0.0660 1.0000 0.0213
-10.750 -0.7732 0.03999 0.03368 -0.0697 0.9943 0.0219
-10.500 -0.7490 0.03749 0.03091 -0.0725 0.9878 0.0228
-10.250 -0.7142 0.03574 0.02915 -0.0751 0.9842 0.0239
-10.000 -0.6825 0.03413 0.02747 -0.0771 0.9788 0.0251
-9.750 -0.6481 0.03256 0.02576 -0.0786 0.9742 0.0262
-9.500 -0.6123 0.03104 0.02422 -0.0799 0.9712 0.0279
-9.250 -0.5870 0.02968 0.02290 -0.0812 0.9628 0.0297
-9.000 -0.5541 0.02820 0.02131 -0.0841 0.9579 0.0326
-8.750 -0.5354 0.02638 0.01959 -0.0858 0.9474 0.0361
-8.500 -0.5031 0.02418 0.01738 -0.0903 0.9429 0.0424
-8.250 -0.4833 0.02236 0.01554 -0.0919 0.9322 0.0507
-8.000 -0.4500 0.02033 0.01355 -0.0961 0.9276 0.0685
-7.750 -0.4324 0.01863 0.01200 -0.0969 0.9161 0.0971
-7.500 -0.4128 0.01627 0.01015 -0.0988 0.9071 0.1831
-7.250 -0.3913 0.01458 0.00931 -0.1001 0.8982 0.3511
-7.000 -0.3598 0.01477 0.00947 -0.1007 0.8901 0.3982
-6.750 -0.3261 0.01504 0.00953 -0.1017 0.8823 0.4234
-6.500 -0.2955 0.01539 0.00975 -0.1019 0.8740 0.4391
-6.250 -0.2635 0.01581 0.01013 -0.1020 0.8660 0.4509
-6.000 -0.2341 0.01622 0.01049 -0.1018 0.8574 0.4614
-5.750 -0.2041 0.01646 0.01057 -0.1019 0.8492 0.4726
-5.500 -0.1757 0.01690 0.01102 -0.1013 0.8405 0.4798
-5.250 -0.1464 0.01696 0.01092 -0.1015 0.8324 0.4889
-5.000 -0.1188 0.01750 0.01150 -0.1005 0.8237 0.4960
-4.750 -0.0900 0.01764 0.01150 -0.1005 0.8158 0.5057
-4.500 -0.0633 0.01784 0.01169 -0.0998 0.8071 0.5100
-4.250 -0.0345 0.01773 0.01146 -0.1000 0.7994 0.5144
-4.000 -0.0084 0.01741 0.01094 -0.1003 0.7908 0.5200
-3.750 0.0201 0.01720 0.01064 -0.1004 0.7833 0.5228
-3.500 0.0465 0.01711 0.01050 -0.1001 0.7751 0.5254
-3.250 0.0748 0.01699 0.01029 -0.1002 0.7674 0.5288
-3.000 0.1018 0.01682 0.01001 -0.1003 0.7595 0.5326
-2.750 0.1302 0.01655 0.00955 -0.1009 0.7518 0.5368
-2.500 0.1576 0.01642 0.00938 -0.1008 0.7446 0.5395
-2.250 0.1846 0.01633 0.00926 -0.1006 0.7366 0.5422
-2.000 0.2132 0.01624 0.00907 -0.1008 0.7299 0.5453
-1.750 0.2398 0.01613 0.00890 -0.1008 0.7217 0.5487
-1.500 0.2705 0.01600 0.00858 -0.1016 0.7158 0.5530
-1.250 0.2954 0.01590 0.00849 -0.1012 0.7071 0.5559
-1.000 0.3244 0.01584 0.00837 -0.1014 0.7008 0.5587
-0.750 0.3505 0.01581 0.00834 -0.1012 0.6931 0.5618
-0.500 0.3792 0.01574 0.00819 -0.1015 0.6863 0.5654
-0.250 0.4072 0.01570 0.00806 -0.1018 0.6794 0.5696
0.000 0.4342 0.01564 0.00799 -0.1017 0.6721 0.5728
0.250 0.4633 0.01564 0.00795 -0.1020 0.6664 0.5759
0.500 0.4887 0.01565 0.00798 -0.1017 0.6584 0.5794
0.750 0.5183 0.01563 0.00787 -0.1021 0.6524 0.5835
1.000 0.5451 0.01565 0.00786 -0.1022 0.6454 0.5875
1.250 0.5723 0.01563 0.00787 -0.1021 0.6388 0.5907
1.500 0.6005 0.01569 0.00791 -0.1022 0.6330 0.5946
1.750 0.6265 0.01574 0.00799 -0.1020 0.6257 0.5990
2.000 0.6565 0.01578 0.00792 -0.1026 0.6202 0.6037
2.250 0.6817 0.01583 0.00806 -0.1023 0.6134 0.6069
2.500 0.7088 0.01587 0.00813 -0.1022 0.6070 0.6109
2.750 0.7383 0.01597 0.00818 -0.1026 0.6018 0.6160
3.000 0.7632 0.01606 0.00833 -0.1023 0.5947 0.6211
3.250 0.7912 0.01611 0.00840 -0.1023 0.5889 0.6252
3.500 0.8175 0.01624 0.00858 -0.1022 0.5829 0.6301
3.750 0.8441 0.01634 0.00870 -0.1022 0.5763 0.6357
4.000 0.8735 0.01641 0.00875 -0.1025 0.5710 0.6405
4.250 0.8966 0.01655 0.00903 -0.1018 0.5640 0.6460
4.500 0.9246 0.01665 0.00912 -0.1020 0.5578 0.6529
4.750 0.9509 0.01677 0.00931 -0.1018 0.5520 0.6582
5.000 0.9752 0.01690 0.00954 -0.1012 0.5450 0.6646
5.250 1.0046 0.01701 0.00961 -0.1016 0.5395 0.6715
5.500 1.0269 0.01717 0.00993 -0.1008 0.5325 0.6781
5.750 1.0537 0.01728 0.01007 -0.1007 0.5259 0.6867
6.000 1.0786 0.01741 0.01030 -0.1002 0.5194 0.6942
6.250 1.1024 0.01753 0.01050 -0.0996 0.5119 0.7034
6.500 1.1297 0.01765 0.01065 -0.0995 0.5056 0.7121
6.750 1.1502 0.01778 0.01095 -0.0983 0.4976 0.7221
7.000 1.1780 0.01789 0.01105 -0.0984 0.4909 0.7340
7.250 1.1959 0.01802 0.01140 -0.0966 0.4824 0.7455
7.500 1.2218 0.01809 0.01148 -0.0963 0.4750 0.7590
7.750 1.2387 0.01822 0.01182 -0.0944 0.4662 0.7739
8.000 1.2631 0.01830 0.01193 -0.0937 0.4585 0.7913
8.250 1.2771 0.01841 0.01227 -0.0913 0.4492 0.8123
8.500 1.2957 0.01847 0.01242 -0.0895 0.4410 0.8390
8.750 1.3053 0.01846 0.01264 -0.0860 0.4318 0.8827
9.000 1.3230 0.01847 0.01277 -0.0843 0.4221 1.0000
9.250 1.3447 0.01873 0.01298 -0.0836 0.4116 1.0000
9.500 1.3566 0.01905 0.01339 -0.0812 0.4001 1.0000
9.750 1.3678 0.01938 0.01375 -0.0786 0.3888 1.0000
10.000 1.3779 0.01978 0.01414 -0.0759 0.3770 1.0000
10.250 1.3864 0.02025 0.01459 -0.0730 0.3644 1.0000
10.500 1.3919 0.02084 0.01524 -0.0699 0.3507 1.0000
10.750 1.3964 0.02155 0.01597 -0.0668 0.3361 1.0000
11.000 1.3995 0.02243 0.01685 -0.0638 0.3209 1.0000
11.250 1.4007 0.02349 0.01789 -0.0608 0.3046 1.0000
11.500 1.4004 0.02478 0.01914 -0.0579 0.2879 1.0000
11.750 1.3991 0.02626 0.02061 -0.0552 0.2704 1.0000
12.000 1.3964 0.02799 0.02231 -0.0528 0.2527 1.0000
12.250 1.3925 0.02995 0.02424 -0.0505 0.2356 1.0000
12.500 1.3875 0.03215 0.02640 -0.0484 0.2190 1.0000
12.750 1.3821 0.03455 0.02875 -0.0466 0.2033 1.0000
13.000 1.3762 0.03712 0.03129 -0.0451 0.1885 1.0000
13.250 1.3701 0.03988 0.03402 -0.0438 0.1745 1.0000
13.500 1.3640 0.04279 0.03690 -0.0427 0.1615 1.0000
13.750 1.3576 0.04587 0.03997 -0.0420 0.1494 1.0000
14.000 1.3505 0.04916 0.04322 -0.0414 0.1386 1.0000
14.250 1.3446 0.05249 0.04655 -0.0410 0.1279 1.0000
14.500 1.3403 0.05579 0.04987 -0.0409 0.1178 1.0000
14.750 1.3346 0.05934 0.05342 -0.0409 0.1090 1.0000
15.000 1.3276 0.06314 0.05721 -0.0411 0.1011 1.0000
15.250 1.3247 0.06662 0.06075 -0.0414 0.0930 1.0000
15.500 1.3176 0.07064 0.06473 -0.0418 0.0864 1.0000
15.750 1.3152 0.07423 0.06840 -0.0424 0.0797 1.0000
16.000 1.3096 0.07823 0.07238 -0.0431 0.0742 1.0000
16.250 1.3073 0.08197 0.07621 -0.0439 0.0687 1.0000
16.500 1.3024 0.08598 0.08017 -0.0447 0.0640 1.0000
16.750 1.3012 0.08972 0.08403 -0.0457 0.0595 1.0000
17.000 1.2973 0.09370 0.08797 -0.0467 0.0557 1.0000
17.250 1.2968 0.09737 0.09175 -0.0477 0.0520 1.0000
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Polar data table (+)
Polar graphs
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