EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 561 AIRFOIL (e561-il) Reynolds number: 50,000 Max Cl/Cd: 26.89 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e561-il-50000-n5.txt Download as CSV file: xf-e561-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 561 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3229 0.10569 0.09874 -0.0531 1.0000 0.0672
-10.500 -0.3421 0.09980 0.09298 -0.0544 1.0000 0.0686
-10.250 -0.3761 0.09148 0.08479 -0.0567 1.0000 0.0694
-10.000 -0.4184 0.08302 0.07644 -0.0588 1.0000 0.0692
-9.750 -0.4667 0.07543 0.06893 -0.0601 1.0000 0.0687
-9.500 -0.5080 0.07040 0.06394 -0.0596 1.0000 0.0680
-9.250 -0.5452 0.06534 0.05884 -0.0606 0.9971 0.0675
-9.000 -0.5521 0.05682 0.04990 -0.0724 0.9829 0.0695
-8.750 -0.5344 0.05278 0.04577 -0.0791 0.9709 0.0736
-8.500 -0.5187 0.04837 0.04106 -0.0854 0.9578 0.0792
-8.250 -0.4946 0.04556 0.03821 -0.0900 0.9468 0.0868
-8.000 -0.4721 0.04287 0.03543 -0.0939 0.9346 0.0969
-7.750 -0.4471 0.04072 0.03320 -0.0975 0.9229 0.1110
-7.500 -0.4173 0.03870 0.03099 -0.1017 0.9124 0.1303
-7.250 -0.3813 0.03846 0.03085 -0.1044 0.9032 0.1506
-7.000 -0.3525 0.03792 0.03020 -0.1060 0.8916 0.1689
-6.750 -0.3140 0.03682 0.02880 -0.1096 0.8839 0.1888
-6.500 -0.2848 0.03678 0.02874 -0.1099 0.8727 0.2023
-6.250 -0.2512 0.03653 0.02839 -0.1111 0.8636 0.2161
-6.000 -0.2167 0.03603 0.02775 -0.1125 0.8546 0.2295
-5.750 -0.1839 0.03531 0.02681 -0.1141 0.8451 0.2427
-5.500 -0.1464 0.03439 0.02561 -0.1165 0.8369 0.2568
-5.250 -0.1151 0.03417 0.02529 -0.1170 0.8270 0.2674
-5.000 -0.0776 0.03358 0.02454 -0.1188 0.8189 0.2787
-4.750 -0.0462 0.03282 0.02352 -0.1202 0.8086 0.2912
-4.500 -0.0096 0.03241 0.02297 -0.1215 0.8007 0.3017
-4.250 0.0191 0.03200 0.02242 -0.1219 0.7900 0.3117
-4.000 0.0588 0.03119 0.02129 -0.1244 0.7824 0.3250
-3.750 0.0838 0.03116 0.02126 -0.1236 0.7712 0.3328
-3.500 0.1232 0.03047 0.02032 -0.1259 0.7640 0.3449
-3.250 0.1477 0.03037 0.02013 -0.1254 0.7526 0.3541
-3.000 0.1865 0.02983 0.01939 -0.1272 0.7456 0.3652
-2.750 0.2104 0.02971 0.01913 -0.1269 0.7342 0.3755
-2.500 0.2478 0.02932 0.01861 -0.1282 0.7275 0.3858
-2.250 0.2716 0.02921 0.01831 -0.1281 0.7160 0.3970
-2.000 0.3056 0.02897 0.01801 -0.1287 0.7091 0.4064
-1.750 0.3288 0.02897 0.01789 -0.1283 0.6984 0.4171
-1.500 0.3645 0.02870 0.01750 -0.1294 0.6920 0.4280
-1.250 0.3849 0.02885 0.01761 -0.1284 0.6812 0.4379
-1.000 0.4208 0.02860 0.01719 -0.1297 0.6748 0.4504
-0.750 0.4399 0.02885 0.01747 -0.1284 0.6649 0.4594
-0.500 0.4737 0.02870 0.01718 -0.1294 0.6582 0.4723
-0.250 0.4949 0.02895 0.01743 -0.1284 0.6492 0.4825
0.000 0.5249 0.02894 0.01734 -0.1287 0.6422 0.4948
0.250 0.5516 0.02909 0.01742 -0.1287 0.6348 0.5078
0.500 0.5755 0.02930 0.01763 -0.1281 0.6270 0.5193
0.750 0.6096 0.02919 0.01745 -0.1289 0.6217 0.5336
1.000 0.6259 0.02973 0.01803 -0.1274 0.6127 0.5461
1.250 0.6557 0.02980 0.01805 -0.1277 0.6067 0.5616
1.500 0.6794 0.03009 0.01837 -0.1271 0.6001 0.5765
1.750 0.6996 0.03049 0.01883 -0.1260 0.5927 0.5914
2.000 0.7309 0.03048 0.01881 -0.1264 0.5877 0.6103
2.250 0.7463 0.03111 0.01955 -0.1247 0.5803 0.6277
2.500 0.7686 0.03144 0.01995 -0.1239 0.5740 0.6487
2.750 0.7991 0.03138 0.01993 -0.1239 0.5696 0.6740
3.000 0.8070 0.03226 0.02100 -0.1212 0.5619 0.6983
3.250 0.8262 0.03255 0.02142 -0.1197 0.5562 0.7314
3.500 0.8516 0.03239 0.02137 -0.1185 0.5522 0.7798
3.750 0.8482 0.03334 0.02260 -0.1139 0.5447 0.8493
4.000 0.8718 0.03374 0.02299 -0.1137 0.5388 1.0000
4.250 0.9112 0.03389 0.02294 -0.1157 0.5348 1.0000
4.500 0.9119 0.03569 0.02480 -0.1131 0.5268 1.0000
4.750 0.9354 0.03644 0.02548 -0.1130 0.5213 1.0000
5.000 0.9726 0.03655 0.02546 -0.1143 0.5176 1.0000
5.250 0.9608 0.03894 0.02795 -0.1104 0.5091 1.0000
5.500 0.9805 0.03982 0.02881 -0.1097 0.5039 1.0000
5.750 1.0194 0.03983 0.02874 -0.1110 0.5005 1.0000
6.000 0.9846 0.04349 0.03253 -0.1050 0.4906 1.0000
6.250 1.0073 0.04423 0.03324 -0.1046 0.4859 1.0000
6.500 1.0477 0.04399 0.03297 -0.1058 0.4831 1.0000
6.750 0.9897 0.05000 0.03914 -0.0997 0.4705 1.0000
7.000 1.0226 0.04997 0.03908 -0.0998 0.4673 1.0000
7.250 1.0653 0.04931 0.03839 -0.1007 0.4652 1.0000
7.500 0.9985 0.05732 0.04655 -0.0964 0.4506 1.0000
7.750 1.0355 0.05671 0.04594 -0.0964 0.4485 1.0000
8.250 1.0148 0.06475 0.05411 -0.0946 0.4316 1.0000
8.750 0.9573 0.07817 0.06770 -0.0947 0.4079 1.0000
9.250 0.9923 0.08077 0.07038 -0.0940 0.3988 1.0000
9.750 0.9846 0.08864 0.07837 -0.0943 0.3833 1.0000
10.000 1.0141 0.08846 0.07824 -0.0936 0.3810 1.0000
10.250 0.9810 0.09615 0.08602 -0.0948 0.3685 1.0000
10.500 1.0064 0.09647 0.08639 -0.0942 0.3655 1.0000
10.750 0.9825 0.10315 0.09315 -0.0955 0.3546 1.0000
11.000 1.0021 0.10418 0.09424 -0.0951 0.3505 1.0000
11.250 1.0274 0.10447 0.09460 -0.0945 0.3477 1.0000
11.750 1.0256 0.11193 0.10222 -0.0956 0.3330 1.0000
12.000 1.0048 0.11854 0.10892 -0.0975 0.3227 1.0000
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Polar data table (+)
Polar graphs
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