EPPLER 553 AIRFOIL (e553-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 553 AIRFOIL (e553-il) Reynolds number: 50,000 Max Cl/Cd: 4.87 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e553-il-50000.txt Download as CSV file: xf-e553-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4368 0.10443 0.09762 -0.0625 1.0000 0.1178
-11.750 -0.4463 0.09832 0.09155 -0.0641 1.0000 0.1159
-11.500 -0.5532 0.08215 0.07538 -0.0752 1.0000 0.1027
-11.250 -0.5741 0.07743 0.07070 -0.0757 1.0000 0.1018
-11.000 -0.5984 0.07336 0.06663 -0.0755 1.0000 0.1008
-10.750 -0.6284 0.07006 0.06334 -0.0741 1.0000 0.1000
-10.500 -0.6599 0.06773 0.06103 -0.0712 1.0000 0.0991
-10.250 -0.6919 0.06600 0.05930 -0.0673 1.0000 0.0980
-10.000 -0.7207 0.06390 0.05713 -0.0635 1.0000 0.0972
-9.750 -0.7452 0.06169 0.05479 -0.0601 1.0000 0.0968
-9.500 -0.7640 0.05930 0.05222 -0.0569 1.0000 0.0968
-9.250 -0.7763 0.05680 0.04950 -0.0543 1.0000 0.0969
-9.000 -0.7829 0.05424 0.04667 -0.0519 1.0000 0.0974
-8.750 -0.7842 0.05171 0.04384 -0.0498 1.0000 0.0985
-8.500 -0.7829 0.04936 0.04113 -0.0478 1.0000 0.1009
-8.250 -0.7776 0.04697 0.03839 -0.0461 1.0000 0.1042
-8.000 -0.7639 0.04510 0.03664 -0.0444 1.0000 0.1098
-7.750 -0.7526 0.04329 0.03454 -0.0425 1.0000 0.1159
-7.500 -0.7384 0.04162 0.03306 -0.0404 1.0000 0.1253
-7.250 -0.7256 0.04013 0.03163 -0.0381 1.0000 0.1369
-7.000 -0.7147 0.03874 0.03037 -0.0357 1.0000 0.1517
-6.750 -0.7067 0.03710 0.02893 -0.0335 1.0000 0.1737
-6.500 -0.7009 0.03486 0.02712 -0.0319 1.0000 0.2089
-6.250 -0.6979 0.03277 0.02681 -0.0297 1.0000 0.3163
-6.000 -0.6882 0.03953 0.03393 -0.0198 1.0000 0.4405
-5.750 -0.6778 0.04463 0.03898 -0.0110 1.0000 0.4734
-5.500 -0.6656 0.04958 0.04388 -0.0015 1.0000 0.4957
-5.250 -0.6565 0.05182 0.04596 0.0042 1.0000 0.5220
-5.000 -0.6426 0.05527 0.04933 0.0124 1.0000 0.5427
-4.750 -0.5934 0.05961 0.05339 0.0162 0.9902 0.5775
-4.500 -0.5438 0.06200 0.05546 0.0172 0.9809 0.6110
-4.250 -0.5233 0.06173 0.05497 0.0168 0.9719 0.6363
-4.000 -0.4657 0.06293 0.05588 0.0160 0.9625 0.6635
-3.750 -0.4390 0.06240 0.05514 0.0148 0.9540 0.6813
-3.500 -0.4118 0.06174 0.05430 0.0134 0.9452 0.6957
-3.250 -0.4246 0.06015 0.05264 0.0152 0.9376 0.7015
-3.000 -0.3857 0.05976 0.05204 0.0125 0.9289 0.7126
-2.750 -0.3953 0.05833 0.05053 0.0143 0.9216 0.7169
-2.500 -0.3693 0.05767 0.04972 0.0126 0.9135 0.7237
-2.250 -0.3636 0.05672 0.04867 0.0132 0.9063 0.7281
-2.000 -0.3559 0.05568 0.04750 0.0126 0.8995 0.7328
-1.750 -0.3385 0.05496 0.04664 0.0112 0.8924 0.7371
-1.500 -0.3260 0.05437 0.04596 0.0114 0.8856 0.7411
-1.250 -0.2965 0.05407 0.04549 0.0083 0.8783 0.7460
-1.000 -0.2910 0.05332 0.04465 0.0082 0.8723 0.7494
-0.750 -0.2668 0.05307 0.04428 0.0062 0.8656 0.7536
-0.500 -0.2477 0.05295 0.04406 0.0054 0.8593 0.7578
-0.250 -0.2321 0.05275 0.04378 0.0044 0.8537 0.7616
0.000 -0.1916 0.05302 0.04388 -0.0007 0.8461 0.7669
0.250 -0.1864 0.05288 0.04371 0.0005 0.8419 0.7706
0.500 -0.1703 0.05301 0.04378 -0.0001 0.8374 0.7747
0.750 -0.1306 0.05360 0.04424 -0.0043 0.8296 0.7801
1.000 -0.1203 0.05380 0.04439 -0.0048 0.8265 0.7846
1.250 -0.1087 0.05415 0.04472 -0.0046 0.8243 0.7891
1.500 -0.0931 0.05471 0.04524 -0.0056 0.8234 0.7941
1.750 -0.0746 0.05544 0.04592 -0.0076 0.8236 0.7994
2.000 -0.0604 0.05630 0.04677 -0.0080 0.8272 0.8045
2.250 -0.1446 0.05615 0.04682 0.0022 0.9425 0.8063
2.500 -0.1230 0.05653 0.04715 0.0004 0.9318 0.8125
2.750 -0.0959 0.05787 0.04845 -0.0022 0.9246 0.8188
3.000 -0.0676 0.05910 0.04966 -0.0048 0.9135 0.8257
3.250 -0.0466 0.05992 0.05045 -0.0065 0.9040 0.8328
3.500 -0.0119 0.06220 0.05270 -0.0099 0.8951 0.8416
3.750 0.0035 0.06244 0.05294 -0.0104 0.8836 0.8493
4.000 0.0258 0.06383 0.05435 -0.0119 0.8758 0.8582
4.250 0.0559 0.06552 0.05605 -0.0146 0.8639 0.8686
4.500 0.0691 0.06608 0.05664 -0.0148 0.8537 0.8790
4.750 0.1002 0.06834 0.05894 -0.0175 0.8455 0.8930
5.000 0.1176 0.06899 0.05967 -0.0181 0.8327 0.9071
5.250 0.1350 0.07008 0.06085 -0.0193 0.8228 0.9240
5.500 0.1789 0.07298 0.06388 -0.0251 0.8128 0.9520
5.750 0.2075 0.07438 0.06535 -0.0290 0.7984 1.0000
6.000 0.2257 0.07569 0.06666 -0.0316 0.7864 1.0000
6.250 0.2555 0.07821 0.06917 -0.0360 0.7762 1.0000
6.500 0.3018 0.08187 0.07283 -0.0426 0.7650 1.0000
6.750 0.3164 0.08317 0.07413 -0.0445 0.7520 1.0000
7.000 0.3377 0.08544 0.07640 -0.0475 0.7405 1.0000
7.250 0.3768 0.08918 0.08012 -0.0526 0.7309 1.0000
7.500 0.4011 0.09147 0.08241 -0.0553 0.7171 1.0000
7.750 0.4113 0.09320 0.08415 -0.0563 0.7046 1.0000
8.000 0.4296 0.09580 0.08674 -0.0581 0.6937 1.0000
8.250 0.4679 0.09982 0.09077 -0.0619 0.6829 1.0000
8.500 0.4773 0.10144 0.09241 -0.0623 0.6692 1.0000
8.750 0.4853 0.10348 0.09448 -0.0628 0.6565 1.0000
9.000 0.5008 0.10631 0.09733 -0.0640 0.6461 1.0000
9.250 0.5357 0.11031 0.10138 -0.0666 0.6344 1.0000
9.500 0.5425 0.11208 0.10319 -0.0668 0.6205 1.0000
9.750 0.5458 0.11420 0.10536 -0.0669 0.6084 1.0000
10.000 0.5590 0.11713 0.10833 -0.0678 0.5973 1.0000
10.250 0.5899 0.12117 0.11246 -0.0698 0.5859 1.0000
10.500 0.6007 0.12346 0.11481 -0.0702 0.5717 1.0000
10.750 0.6001 0.12551 0.11691 -0.0703 0.5593 1.0000
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Polar data table (+)
Polar graphs
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