EPPLER 553 AIRFOIL (e553-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 553 AIRFOIL (e553-il) Reynolds number: 100,000 Max Cl/Cd: 49.22 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e553-il-100000-n5.txt Download as CSV file: xf-e553-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.5138 0.10560 0.09999 -0.0613 1.0000 0.0197
-14.500 -0.5686 0.09091 0.08491 -0.0697 1.0000 0.0189
-14.250 -0.5913 0.08383 0.07763 -0.0733 1.0000 0.0188
-14.000 -0.6084 0.07816 0.07176 -0.0758 1.0000 0.0187
-13.750 -0.6188 0.07386 0.06734 -0.0774 1.0000 0.0189
-13.500 -0.6278 0.07001 0.06337 -0.0785 1.0000 0.0191
-13.250 -0.6356 0.06643 0.05965 -0.0792 1.0000 0.0192
-13.000 -0.6409 0.06328 0.05637 -0.0796 1.0000 0.0193
-12.750 -0.6448 0.06042 0.05341 -0.0797 1.0000 0.0196
-12.500 -0.6471 0.05787 0.05075 -0.0795 1.0000 0.0199
-12.250 -0.6492 0.05543 0.04821 -0.0791 1.0000 0.0205
-12.000 -0.6513 0.05315 0.04580 -0.0784 1.0000 0.0213
-11.750 -0.6511 0.05111 0.04360 -0.0773 1.0000 0.0220
-11.500 -0.6502 0.04933 0.04173 -0.0759 1.0000 0.0227
-11.250 -0.6506 0.04782 0.04026 -0.0745 1.0000 0.0234
-11.000 -0.6502 0.04650 0.03892 -0.0724 1.0000 0.0239
-10.750 -0.6544 0.04524 0.03766 -0.0700 1.0000 0.0248
-10.500 -0.6599 0.04421 0.03661 -0.0669 1.0000 0.0254
-10.250 -0.6465 0.04291 0.03521 -0.0665 0.9968 0.0265
-10.000 -0.6213 0.04126 0.03356 -0.0684 0.9895 0.0281
-9.750 -0.5983 0.03958 0.03183 -0.0708 0.9809 0.0307
-9.500 -0.5771 0.03789 0.03009 -0.0729 0.9711 0.0341
-9.250 -0.5580 0.03626 0.02842 -0.0745 0.9604 0.0376
-9.000 -0.5411 0.03450 0.02664 -0.0762 0.9495 0.0416
-8.750 -0.5225 0.03266 0.02476 -0.0783 0.9399 0.0477
-8.500 -0.5055 0.03074 0.02279 -0.0805 0.9293 0.0557
-8.250 -0.4896 0.02867 0.02071 -0.0827 0.9175 0.0664
-8.000 -0.4717 0.02676 0.01884 -0.0848 0.9078 0.0822
-7.750 -0.4545 0.02491 0.01708 -0.0863 0.8976 0.1087
-7.500 -0.4411 0.02305 0.01542 -0.0871 0.8863 0.1512
-7.250 -0.4233 0.02078 0.01369 -0.0890 0.8782 0.2425
-7.000 -0.4027 0.02037 0.01377 -0.0886 0.8679 0.3410
-6.750 -0.3684 0.02043 0.01371 -0.0899 0.8617 0.3861
-6.500 -0.3417 0.02063 0.01373 -0.0897 0.8521 0.4108
-6.000 -0.2810 0.02123 0.01400 -0.0901 0.8363 0.4436
-5.750 -0.2474 0.02140 0.01397 -0.0909 0.8302 0.4571
-5.500 -0.2222 0.02178 0.01425 -0.0900 0.8205 0.4690
-5.250 -0.1891 0.02221 0.01460 -0.0901 0.8142 0.4781
-5.000 -0.1651 0.02191 0.01407 -0.0901 0.8047 0.4876
-4.750 -0.1333 0.02188 0.01393 -0.0905 0.7981 0.4908
-4.500 -0.1081 0.02179 0.01374 -0.0900 0.7891 0.4944
-4.250 -0.0779 0.02148 0.01324 -0.0907 0.7822 0.4990
-4.000 -0.0525 0.02109 0.01263 -0.0911 0.7735 0.5044
-3.750 -0.0230 0.02095 0.01239 -0.0912 0.7665 0.5068
-3.500 0.0031 0.02083 0.01220 -0.0910 0.7584 0.5098
-3.250 0.0316 0.02065 0.01187 -0.0913 0.7511 0.5136
-3.000 0.0589 0.02040 0.01147 -0.0916 0.7435 0.5179
-2.750 0.0867 0.02017 0.01109 -0.0920 0.7360 0.5215
-2.500 0.1146 0.02008 0.01094 -0.0920 0.7292 0.5241
-2.250 0.1408 0.02001 0.01081 -0.0918 0.7212 0.5273
-2.000 0.1707 0.01986 0.01053 -0.0923 0.7153 0.5309
-1.750 0.1960 0.01974 0.01031 -0.0922 0.7068 0.5348
-1.500 0.2256 0.01959 0.01004 -0.0927 0.7006 0.5383
-1.250 0.2507 0.01959 0.01004 -0.0923 0.6929 0.5411
-1.000 0.2786 0.01954 0.00993 -0.0924 0.6862 0.5445
-0.750 0.3059 0.01949 0.00981 -0.0925 0.6795 0.5482
-0.500 0.3331 0.01942 0.00966 -0.0927 0.6722 0.5523
-0.250 0.3626 0.01935 0.00951 -0.0931 0.6666 0.5556
0.000 0.3867 0.01941 0.00961 -0.0925 0.6587 0.5587
0.250 0.4152 0.01939 0.00954 -0.0927 0.6528 0.5625
0.500 0.4413 0.01942 0.00954 -0.0926 0.6458 0.5667
0.750 0.4690 0.01941 0.00948 -0.0929 0.6391 0.5709
1.000 0.4969 0.01942 0.00948 -0.0929 0.6335 0.5739
1.250 0.5212 0.01952 0.00962 -0.0924 0.6261 0.5777
1.500 0.5498 0.01953 0.00961 -0.0927 0.6205 0.5823
1.750 0.5760 0.01962 0.00968 -0.0927 0.6138 0.5873
2.000 0.6017 0.01970 0.00980 -0.0923 0.6074 0.5907
2.250 0.6306 0.01973 0.00981 -0.0926 0.6023 0.5947
2.500 0.6539 0.01989 0.01006 -0.0920 0.5950 0.5994
2.750 0.6818 0.01997 0.01011 -0.0922 0.5893 0.6047
3.000 0.7073 0.02009 0.01031 -0.0919 0.5834 0.6089
3.250 0.7316 0.02025 0.01054 -0.0914 0.5769 0.6140
3.500 0.7606 0.02033 0.01059 -0.0918 0.5717 0.6200
3.750 0.7834 0.02053 0.01091 -0.0911 0.5651 0.6243
4.000 0.8087 0.02069 0.01113 -0.0908 0.5591 0.6298
4.250 0.8382 0.02079 0.01120 -0.0912 0.5542 0.6367
4.500 0.8583 0.02106 0.01165 -0.0900 0.5470 0.6419
4.750 0.8847 0.02120 0.01185 -0.0899 0.5413 0.6486
5.000 0.9097 0.02140 0.01211 -0.0895 0.5354 0.6552
5.250 0.9316 0.02163 0.01248 -0.0887 0.5286 0.6617
5.500 0.9602 0.02175 0.01261 -0.0889 0.5231 0.6700
5.750 0.9794 0.02206 0.01309 -0.0876 0.5159 0.6771
6.000 1.0047 0.02225 0.01335 -0.0873 0.5096 0.6864
6.250 1.0277 0.02247 0.01369 -0.0866 0.5034 0.6946
6.500 1.0486 0.02275 0.01410 -0.0856 0.4961 0.7043
6.750 1.0759 0.02285 0.01426 -0.0855 0.4904 0.7148
7.000 1.0911 0.02323 0.01485 -0.0836 0.4820 0.7256
7.250 1.1164 0.02334 0.01502 -0.0831 0.4754 0.7386
7.500 1.1311 0.02371 0.01559 -0.0812 0.4669 0.7525
7.750 1.1540 0.02382 0.01579 -0.0803 0.4597 0.7683
8.000 1.1663 0.02418 0.01637 -0.0778 0.4511 0.7863
8.250 1.1864 0.02426 0.01655 -0.0764 0.4435 0.8091
8.500 1.1933 0.02460 0.01713 -0.0730 0.4345 0.8410
8.750 1.2084 0.02455 0.01723 -0.0705 0.4266 0.9067
9.000 1.2168 0.02502 0.01784 -0.0679 0.4165 1.0000
9.250 1.2313 0.02550 0.01836 -0.0663 0.4068 1.0000
9.500 1.2456 0.02597 0.01884 -0.0646 0.3967 1.0000
9.750 1.2525 0.02673 0.01971 -0.0621 0.3857 1.0000
10.000 1.2623 0.02744 0.02047 -0.0600 0.3748 1.0000
10.250 1.2719 0.02815 0.02120 -0.0580 0.3635 1.0000
10.500 1.2763 0.02917 0.02230 -0.0557 0.3512 1.0000
10.750 1.2797 0.03034 0.02352 -0.0534 0.3383 1.0000
11.000 1.2828 0.03161 0.02484 -0.0513 0.3252 1.0000
11.250 1.2847 0.03305 0.02631 -0.0494 0.3114 1.0000
11.500 1.2857 0.03467 0.02797 -0.0475 0.2973 1.0000
11.750 1.2852 0.03651 0.02981 -0.0458 0.2826 1.0000
12.000 1.2836 0.03855 0.03186 -0.0443 0.2676 1.0000
12.250 1.2812 0.04079 0.03409 -0.0429 0.2528 1.0000
12.500 1.2778 0.04324 0.03653 -0.0418 0.2382 1.0000
12.750 1.2738 0.04587 0.03915 -0.0408 0.2242 1.0000
13.000 1.2690 0.04872 0.04198 -0.0400 0.2106 1.0000
13.500 1.2590 0.05489 0.04817 -0.0391 0.1849 1.0000
13.750 1.2545 0.05815 0.05146 -0.0390 0.1730 1.0000
14.000 1.2496 0.06156 0.05488 -0.0390 0.1619 1.0000
14.250 1.2444 0.06511 0.05843 -0.0392 0.1515 1.0000
14.500 1.2394 0.06878 0.06211 -0.0396 0.1416 1.0000
14.750 1.2358 0.07240 0.06579 -0.0401 0.1321 1.0000
15.000 1.2312 0.07622 0.06962 -0.0407 0.1236 1.0000
15.250 1.2269 0.08012 0.07356 -0.0415 0.1154 1.0000
15.500 1.2236 0.08396 0.07746 -0.0423 0.1077 1.0000
15.750 1.2188 0.08806 0.08156 -0.0434 0.1010 1.0000
16.000 1.2166 0.09192 0.08552 -0.0444 0.0942 1.0000
16.250 1.2119 0.09615 0.08977 -0.0457 0.0885 1.0000
16.500 1.2099 0.10010 0.09382 -0.0469 0.0824 1.0000
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Polar data table (+)
Polar graphs
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