EPPLER 553 AIRFOIL (e553-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 553 AIRFOIL (e553-il) Reynolds number: 200,000 Max Cl/Cd: 69.38 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e553-il-200000-n5.txt Download as CSV file: xf-e553-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.5851 0.12012 0.11571 -0.0509 1.0000 0.0094
-16.500 -0.6077 0.11105 0.10648 -0.0555 1.0000 0.0094
-16.250 -0.6271 0.10310 0.09836 -0.0596 1.0000 0.0093
-16.000 -0.6412 0.09665 0.09177 -0.0628 1.0000 0.0093
-15.750 -0.6553 0.09046 0.08542 -0.0658 1.0000 0.0093
-15.500 -0.6671 0.08497 0.07976 -0.0683 1.0000 0.0093
-15.250 -0.6774 0.07995 0.07458 -0.0705 1.0000 0.0094
-15.000 -0.6837 0.07578 0.07027 -0.0721 1.0000 0.0094
-14.750 -0.6898 0.07182 0.06621 -0.0735 1.0000 0.0096
-14.500 -0.6922 0.06849 0.06272 -0.0743 1.0000 0.0095
-14.250 -0.6941 0.06544 0.05967 -0.0754 1.0000 0.0098
-14.000 -0.6952 0.06256 0.05672 -0.0760 1.0000 0.0099
-13.750 -0.6960 0.05984 0.05395 -0.0767 1.0000 0.0103
-13.500 -0.6965 0.05726 0.05129 -0.0769 1.0000 0.0105
-13.250 -0.6961 0.05492 0.04885 -0.0768 1.0000 0.0106
-13.000 -0.6955 0.05273 0.04658 -0.0768 1.0000 0.0109
-12.750 -0.6949 0.05060 0.04435 -0.0764 1.0000 0.0114
-12.500 -0.6931 0.04874 0.04242 -0.0756 1.0000 0.0114
-12.250 -0.6917 0.04690 0.04048 -0.0747 1.0000 0.0119
-12.000 -0.6913 0.04515 0.03868 -0.0736 1.0000 0.0122
-11.750 -0.6919 0.04350 0.03702 -0.0723 1.0000 0.0123
-11.500 -0.6943 0.04193 0.03546 -0.0707 1.0000 0.0126
-11.000 -0.6707 0.03825 0.03169 -0.0730 0.9931 0.0133
-10.750 -0.6515 0.03619 0.02955 -0.0755 0.9843 0.0141
-10.500 -0.6347 0.03427 0.02753 -0.0775 0.9721 0.0147
-10.250 -0.6184 0.03229 0.02549 -0.0796 0.9600 0.0152
-10.000 -0.5994 0.03031 0.02346 -0.0822 0.9491 0.0162
-9.750 -0.5754 0.02844 0.02149 -0.0855 0.9400 0.0176
-9.500 -0.5494 0.02658 0.01956 -0.0892 0.9301 0.0200
-9.250 -0.5241 0.02487 0.01774 -0.0925 0.9186 0.0227
-9.000 -0.5013 0.02311 0.01589 -0.0956 0.9060 0.0256
-8.750 -0.4767 0.02159 0.01427 -0.0984 0.8941 0.0297
-8.500 -0.4551 0.02045 0.01307 -0.0996 0.8813 0.0359
-8.250 -0.4353 0.01947 0.01205 -0.1001 0.8690 0.0445
-8.000 -0.4147 0.01860 0.01114 -0.1004 0.8577 0.0560
-7.750 -0.3946 0.01770 0.01027 -0.1005 0.8470 0.0740
-7.500 -0.3769 0.01684 0.00948 -0.1000 0.8359 0.0995
-7.250 -0.3581 0.01586 0.00863 -0.0999 0.8260 0.1393
-7.000 -0.3407 0.01468 0.00771 -0.0997 0.8161 0.2054
-6.750 -0.3228 0.01360 0.00710 -0.0994 0.8066 0.3063
-6.500 -0.2964 0.01340 0.00697 -0.0994 0.7983 0.3580
-6.250 -0.2698 0.01337 0.00688 -0.0993 0.7894 0.3830
-6.000 -0.2415 0.01340 0.00679 -0.0994 0.7816 0.4018
-5.750 -0.2144 0.01346 0.00675 -0.0992 0.7728 0.4161
-5.500 -0.1861 0.01351 0.00666 -0.0992 0.7652 0.4273
-5.250 -0.1588 0.01357 0.00656 -0.0992 0.7567 0.4383
-5.000 -0.1308 0.01377 0.00672 -0.0990 0.7492 0.4498
-4.750 -0.1035 0.01389 0.00676 -0.0988 0.7411 0.4591
-4.500 -0.0755 0.01387 0.00662 -0.0988 0.7337 0.4632
-4.250 -0.0479 0.01379 0.00642 -0.0989 0.7258 0.4669
-4.000 -0.0199 0.01370 0.00616 -0.0990 0.7184 0.4706
-3.750 0.0078 0.01363 0.00601 -0.0990 0.7110 0.4729
-3.500 0.0354 0.01358 0.00589 -0.0990 0.7035 0.4754
-3.250 0.0633 0.01354 0.00577 -0.0990 0.6967 0.4783
-3.000 0.0909 0.01349 0.00563 -0.0991 0.6890 0.4813
-2.750 0.1191 0.01345 0.00546 -0.0992 0.6825 0.4843
-2.250 0.1746 0.01337 0.00524 -0.0993 0.6684 0.4899
-2.000 0.2020 0.01335 0.00519 -0.0993 0.6612 0.4925
-1.750 0.2297 0.01334 0.00511 -0.0993 0.6543 0.4952
-1.500 0.2575 0.01333 0.00504 -0.0993 0.6478 0.4981
-1.250 0.2851 0.01333 0.00497 -0.0994 0.6407 0.5013
-1.000 0.3132 0.01334 0.00487 -0.0995 0.6347 0.5045
-0.750 0.3403 0.01333 0.00489 -0.0994 0.6275 0.5070
-0.500 0.3678 0.01335 0.00488 -0.0994 0.6211 0.5098
-0.250 0.3953 0.01338 0.00487 -0.0994 0.6148 0.5127
0.000 0.4227 0.01340 0.00486 -0.0994 0.6080 0.5158
0.250 0.4505 0.01345 0.00483 -0.0995 0.6022 0.5192
0.500 0.4776 0.01347 0.00488 -0.0994 0.5954 0.5223
0.750 0.5047 0.01352 0.00492 -0.0994 0.5892 0.5252
1.000 0.5319 0.01357 0.00497 -0.0993 0.5832 0.5285
1.250 0.5590 0.01363 0.00502 -0.0993 0.5768 0.5319
1.500 0.5865 0.01371 0.00504 -0.0993 0.5713 0.5354
1.750 0.6133 0.01376 0.00513 -0.0992 0.5649 0.5386
2.000 0.6401 0.01383 0.00523 -0.0991 0.5589 0.5419
2.250 0.6672 0.01393 0.00532 -0.0990 0.5537 0.5457
2.500 0.6938 0.01401 0.00544 -0.0989 0.5474 0.5499
3.000 0.7472 0.01420 0.00566 -0.0987 0.5362 0.5571
3.250 0.7733 0.01430 0.00582 -0.0985 0.5301 0.5609
3.500 0.7998 0.01442 0.00595 -0.0983 0.5246 0.5655
3.750 0.8262 0.01455 0.00610 -0.0982 0.5189 0.5705
4.000 0.8518 0.01465 0.00629 -0.0979 0.5129 0.5745
4.250 0.8778 0.01479 0.00645 -0.0977 0.5074 0.5791
4.500 0.9033 0.01492 0.00665 -0.0974 0.5011 0.5842
4.750 0.9285 0.01506 0.00683 -0.0970 0.4948 0.5889
5.000 0.9539 0.01521 0.00704 -0.0967 0.4892 0.5939
5.250 0.9785 0.01536 0.00728 -0.0962 0.4825 0.6000
5.500 1.0033 0.01553 0.00748 -0.0958 0.4766 0.6059
5.750 1.0275 0.01569 0.00775 -0.0953 0.4703 0.6118
6.000 1.0513 0.01587 0.00798 -0.0947 0.4632 0.6186
6.250 1.0748 0.01605 0.00823 -0.0940 0.4565 0.6247
6.500 1.0973 0.01623 0.00851 -0.0932 0.4487 0.6320
6.750 1.1199 0.01644 0.00877 -0.0924 0.4418 0.6397
7.000 1.1414 0.01663 0.00909 -0.0914 0.4337 0.6482
7.250 1.1626 0.01686 0.00936 -0.0903 0.4263 0.6570
7.500 1.1825 0.01708 0.00971 -0.0891 0.4172 0.6666
7.750 1.2017 0.01732 0.01003 -0.0877 0.4087 0.6761
8.000 1.2197 0.01758 0.01038 -0.0861 0.3992 0.6873
8.250 1.2358 0.01784 0.01075 -0.0842 0.3900 0.6996
8.500 1.2496 0.01813 0.01111 -0.0819 0.3804 0.7131
8.750 1.2637 0.01845 0.01156 -0.0797 0.3697 0.7285
9.000 1.2765 0.01883 0.01203 -0.0773 0.3586 0.7460
9.250 1.2874 0.01928 0.01255 -0.0748 0.3468 0.7665
9.500 1.2963 0.01977 0.01314 -0.0719 0.3340 0.7915
9.750 1.3036 0.02027 0.01377 -0.0689 0.3205 0.8289
10.000 1.3068 0.02066 0.01435 -0.0652 0.3068 1.0000
10.250 1.3139 0.02156 0.01522 -0.0628 0.2913 1.0000
10.500 1.3185 0.02265 0.01626 -0.0604 0.2744 1.0000
10.750 1.3216 0.02390 0.01746 -0.0580 0.2579 1.0000
11.000 1.3235 0.02532 0.01884 -0.0557 0.2409 1.0000
11.250 1.3248 0.02689 0.02037 -0.0535 0.2247 1.0000
11.500 1.3251 0.02863 0.02208 -0.0516 0.2087 1.0000
11.750 1.3247 0.03054 0.02395 -0.0498 0.1934 1.0000
12.000 1.3241 0.03258 0.02596 -0.0482 0.1794 1.0000
12.250 1.3227 0.03478 0.02814 -0.0467 0.1664 1.0000
12.750 1.3204 0.03947 0.03281 -0.0445 0.1425 1.0000
13.000 1.3199 0.04190 0.03527 -0.0437 0.1320 1.0000
13.250 1.3181 0.04455 0.03793 -0.0430 0.1223 1.0000
13.750 1.3152 0.05012 0.04353 -0.0421 0.1043 1.0000
14.000 1.3136 0.05307 0.04650 -0.0419 0.0969 1.0000
14.250 1.3114 0.05618 0.04963 -0.0418 0.0892 1.0000
14.500 1.3108 0.05920 0.05270 -0.0419 0.0825 1.0000
14.750 1.3076 0.06261 0.05612 -0.0421 0.0763 1.0000
15.000 1.3078 0.06570 0.05929 -0.0424 0.0705 1.0000
15.250 1.3044 0.06932 0.06294 -0.0429 0.0654 1.0000
15.500 1.3043 0.07259 0.06629 -0.0434 0.0605 1.0000
15.750 1.3014 0.07630 0.07004 -0.0441 0.0563 1.0000
16.000 1.3000 0.07989 0.07370 -0.0449 0.0523 1.0000
16.250 1.2980 0.08363 0.07751 -0.0458 0.0486 1.0000
16.500 1.2942 0.08771 0.08163 -0.0469 0.0456 1.0000
16.750 1.2936 0.09135 0.08538 -0.0479 0.0425 1.0000
17.000 1.2902 0.09548 0.08957 -0.0492 0.0398 1.0000
17.250 1.2867 0.09971 0.09386 -0.0506 0.0375 1.0000
17.500 1.2855 0.10362 0.09788 -0.0519 0.0352 1.0000
17.750 1.2817 0.10796 0.10230 -0.0535 0.0331 1.0000
18.000 1.2770 0.11253 0.10693 -0.0554 0.0316 1.0000
18.250 1.2760 0.11651 0.11104 -0.0570 0.0297 1.0000
18.500 1.2734 0.12081 0.11543 -0.0588 0.0281 1.0000
18.750 1.2687 0.12551 0.12019 -0.0610 0.0268 1.0000
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