E61 (5.64%) (e61-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E61 (5.64%) (e61-il) Reynolds number: 500,000 Max Cl/Cd: 157.06 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e61-il-500000-n5.txt Download as CSV file: xf-e61-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E61 (5.64%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.0727 0.09337 0.09104 -0.0790 0.9659 0.0064
-9.000 -0.0639 0.09013 0.08780 -0.0804 0.9639 0.0066
-8.750 -0.0538 0.08670 0.08437 -0.0823 0.9623 0.0069
-8.500 -0.0427 0.08322 0.08090 -0.0844 0.9611 0.0072
-8.250 -0.0298 0.07976 0.07744 -0.0870 0.9600 0.0084
-7.500 -0.0881 0.08858 0.08615 -0.0846 0.9612 0.0068
-7.000 0.0032 0.06447 0.06220 -0.0911 0.9400 0.0084
-6.000 -0.0178 0.06900 0.06664 -0.0991 0.9353 0.0053
-5.750 -0.0096 0.06684 0.06449 -0.0997 0.9273 0.0056
-5.500 0.0138 0.06339 0.06103 -0.1048 0.9244 0.0058
-5.250 0.0423 0.05955 0.05717 -0.1113 0.9224 0.0062
-5.000 0.0591 0.05679 0.05441 -0.1141 0.9144 0.0071
-4.750 0.1030 0.05211 0.04968 -0.1248 0.9116 0.0088
-4.500 0.1421 0.04719 0.04471 -0.1339 0.9098 0.0084
-4.250 0.1804 0.04252 0.03995 -0.1423 0.9039 0.0084
-4.000 0.2395 0.03634 0.03364 -0.1556 0.9012 0.0089
-3.750 0.2976 0.03086 0.02800 -0.1682 0.8996 0.0105
-3.500 0.3438 0.02829 0.02530 -0.1749 0.8981 0.0139
-3.250 0.4148 0.02166 0.01826 -0.1882 0.8978 0.0130
-3.000 0.4810 0.01602 0.01197 -0.1985 0.8977 0.0126
-2.750 0.5307 0.01349 0.00896 -0.2039 0.8968 0.0137
-2.500 0.5695 0.01221 0.00738 -0.2066 0.8931 0.0144
-2.250 0.6041 0.01188 0.00689 -0.2081 0.8884 0.0159
-2.000 0.6471 0.01067 0.00541 -0.2116 0.8856 0.0156
-1.750 0.6913 0.00971 0.00425 -0.2154 0.8829 0.0153
-1.500 0.7264 0.00912 0.00355 -0.2171 0.8763 0.0151
-1.250 0.7658 0.00864 0.00296 -0.2197 0.8707 0.0149
-1.000 0.8004 0.00831 0.00255 -0.2213 0.8627 0.0149
-0.750 0.8360 0.00806 0.00221 -0.2230 0.8541 0.0151
-0.500 0.8688 0.00793 0.00197 -0.2241 0.8436 0.0155
-0.250 0.8991 0.00787 0.00181 -0.2246 0.8321 0.0161
0.000 0.9287 0.00784 0.00167 -0.2249 0.8205 0.0205
0.250 0.9577 0.00781 0.00166 -0.2252 0.8087 0.0502
0.500 0.9885 0.00754 0.00180 -0.2263 0.7963 0.2469
0.750 1.0171 0.00745 0.00193 -0.2266 0.7833 0.3755
1.000 1.0396 0.00672 0.00226 -0.2256 0.7705 0.8902
1.500 1.0884 0.00693 0.00234 -0.2240 0.7423 1.0000
1.750 1.1137 0.00710 0.00243 -0.2234 0.7275 1.0000
2.000 1.1387 0.00727 0.00256 -0.2228 0.7121 1.0000
2.250 1.1630 0.00748 0.00268 -0.2220 0.6945 1.0000
2.500 1.1867 0.00769 0.00281 -0.2212 0.6743 1.0000
2.750 1.2097 0.00795 0.00297 -0.2201 0.6524 1.0000
3.000 1.2323 0.00822 0.00315 -0.2190 0.6273 1.0000
3.250 1.2533 0.00858 0.00340 -0.2176 0.5958 1.0000
3.500 1.2726 0.00904 0.00367 -0.2158 0.5545 1.0000
3.750 1.2910 0.00959 0.00400 -0.2139 0.5069 1.0000
4.000 1.3091 0.01022 0.00439 -0.2120 0.4584 1.0000
4.250 1.3219 0.01132 0.00499 -0.2092 0.3690 1.0000
4.500 1.3336 0.01266 0.00571 -0.2064 0.2645 1.0000
4.750 1.3502 0.01361 0.00630 -0.2045 0.2006 1.0000
5.000 1.3658 0.01467 0.00701 -0.2025 0.1343 1.0000
5.250 1.3795 0.01591 0.00782 -0.2001 0.0661 1.0000
5.500 1.3946 0.01695 0.00860 -0.1978 0.0235 1.0000
5.750 1.4116 0.01779 0.00933 -0.1958 0.0064 1.0000
6.000 1.4311 0.01834 0.00995 -0.1942 0.0042 1.0000
6.250 1.4503 0.01888 0.01058 -0.1926 0.0038 1.0000
6.500 1.4689 0.01949 0.01129 -0.1908 0.0035 1.0000
6.750 1.4865 0.02020 0.01211 -0.1889 0.0031 1.0000
7.000 1.5031 0.02100 0.01302 -0.1869 0.0029 1.0000
7.250 1.5186 0.02189 0.01408 -0.1846 0.0027 1.0000
7.500 1.5330 0.02289 0.01520 -0.1822 0.0025 1.0000
7.750 1.5461 0.02401 0.01645 -0.1796 0.0025 1.0000
8.000 1.5579 0.02524 0.01780 -0.1769 0.0024 1.0000
8.250 1.5683 0.02662 0.01931 -0.1739 0.0023 1.0000
8.500 1.5780 0.02811 0.02094 -0.1710 0.0023 1.0000
8.750 1.5866 0.02974 0.02271 -0.1679 0.0023 1.0000
9.000 1.5954 0.03144 0.02457 -0.1650 0.0023 1.0000
9.250 1.6034 0.03334 0.02663 -0.1620 0.0023 1.0000
9.500 1.6117 0.03536 0.02883 -0.1592 0.0023 1.0000
9.750 1.6197 0.03757 0.03127 -0.1564 0.0023 1.0000
10.000 1.6276 0.03995 0.03385 -0.1538 0.0023 1.0000
10.250 1.6346 0.04258 0.03672 -0.1511 0.0023 1.0000
10.500 1.6400 0.04507 0.03941 -0.1485 0.0023 1.0000
10.750 1.6429 0.04778 0.04234 -0.1458 0.0022 1.0000
11.000 1.6437 0.05077 0.04556 -0.1431 0.0021 1.0000
11.250 1.6415 0.05396 0.04895 -0.1404 0.0020 1.0000
11.500 1.6330 0.05820 0.05344 -0.1376 0.0019 1.0000
11.750 1.6213 0.06302 0.05856 -0.1349 0.0019 1.0000
12.000 1.5987 0.06970 0.06561 -0.1323 0.0018 1.0000
12.250 1.5754 0.07636 0.07260 -0.1307 0.0017 1.0000
13.000 1.5334 0.09312 0.09002 -0.1311 0.0017 1.0000
13.500 1.3298 0.11123 0.10879 -0.1231 0.0021 1.0000
13.750 1.2808 0.12376 0.12157 -0.1295 0.0017 1.0000
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Polar data table (+)
Polar graphs
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