EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 560 AIRFOIL (e560-il) Reynolds number: 50,000 Max Cl/Cd: 31.07 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e560-il-50000-n5.txt Download as CSV file: xf-e560-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 560 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3403 0.11387 0.10648 -0.0499 1.0000 0.0735
-11.000 -0.3536 0.10828 0.10097 -0.0515 1.0000 0.0755
-10.750 -0.3805 0.10010 0.09292 -0.0544 1.0000 0.0773
-10.500 -0.3665 0.10080 0.09367 -0.0521 1.0000 0.0803
-10.250 -0.3721 0.09765 0.09060 -0.0520 1.0000 0.0831
-10.000 -0.3947 0.09166 0.08474 -0.0533 1.0000 0.0857
-9.750 -0.4465 0.08125 0.07452 -0.0566 1.0000 0.0873
-9.500 -0.5019 0.07239 0.06579 -0.0585 1.0000 0.0870
-9.250 -0.5507 0.06651 0.05999 -0.0580 1.0000 0.0861
-9.000 -0.5966 0.06063 0.05412 -0.0587 1.0000 0.0852
-8.750 -0.6270 0.05420 0.04751 -0.0628 1.0000 0.0859
-8.500 -0.6279 0.04938 0.04245 -0.0677 0.9969 0.0905
-8.250 -0.6005 0.04535 0.03811 -0.0757 0.9877 0.1016
-8.000 -0.5687 0.04315 0.03578 -0.0812 0.9790 0.1149
-7.750 -0.5337 0.04238 0.03503 -0.0853 0.9704 0.1302
-7.500 -0.4995 0.04199 0.03463 -0.0883 0.9612 0.1457
-7.250 -0.4675 0.04099 0.03346 -0.0913 0.9515 0.1600
-7.000 -0.4341 0.03974 0.03197 -0.0945 0.9424 0.1738
-6.750 -0.3970 0.03856 0.03053 -0.0981 0.9343 0.1879
-6.500 -0.3677 0.03901 0.03105 -0.0978 0.9238 0.1971
-6.250 -0.3332 0.03821 0.03006 -0.1002 0.9150 0.2090
-6.000 -0.2981 0.03715 0.02875 -0.1029 0.9060 0.2219
-5.750 -0.2650 0.03604 0.02731 -0.1055 0.8962 0.2352
-5.500 -0.2286 0.03611 0.02742 -0.1064 0.8885 0.2442
-5.250 -0.1988 0.03538 0.02649 -0.1077 0.8777 0.2553
-5.000 -0.1563 0.03435 0.02516 -0.1112 0.8715 0.2688
-4.750 -0.1300 0.03428 0.02508 -0.1108 0.8599 0.2770
-4.500 -0.0903 0.03349 0.02408 -0.1133 0.8531 0.2886
-4.250 -0.0572 0.03271 0.02302 -0.1151 0.8427 0.3012
-4.000 -0.0232 0.03248 0.02279 -0.1158 0.8346 0.3095
-3.750 0.0121 0.03184 0.02195 -0.1175 0.8254 0.3209
-3.500 0.0469 0.03135 0.02130 -0.1189 0.8164 0.3317
-3.250 0.0829 0.03093 0.02079 -0.1202 0.8079 0.3413
-3.000 0.1171 0.03041 0.02005 -0.1218 0.7981 0.3531
-2.750 0.1543 0.03001 0.01961 -0.1231 0.7902 0.3624
-2.500 0.1846 0.02969 0.01914 -0.1237 0.7794 0.3727
-2.250 0.2249 0.02916 0.01844 -0.1258 0.7722 0.3843
-2.000 0.2510 0.02903 0.01828 -0.1255 0.7606 0.3928
-1.750 0.2922 0.02851 0.01756 -0.1278 0.7535 0.4054
-1.500 0.3170 0.02848 0.01752 -0.1272 0.7419 0.4137
-1.250 0.3498 0.02824 0.01716 -0.1281 0.7325 0.4249
-1.000 0.3830 0.02802 0.01684 -0.1289 0.7232 0.4361
-0.750 0.4099 0.02800 0.01679 -0.1287 0.7128 0.4456
-0.500 0.4465 0.02773 0.01638 -0.1301 0.7047 0.4582
-0.250 0.4704 0.02783 0.01647 -0.1294 0.6936 0.4683
0.000 0.5078 0.02757 0.01612 -0.1307 0.6865 0.4806
0.250 0.5303 0.02778 0.01629 -0.1301 0.6752 0.4923
0.500 0.5620 0.02772 0.01617 -0.1305 0.6670 0.5047
0.750 0.5875 0.02784 0.01630 -0.1301 0.6572 0.5166
1.000 0.6163 0.02791 0.01634 -0.1302 0.6488 0.5302
1.250 0.6437 0.02803 0.01644 -0.1302 0.6398 0.5444
1.500 0.6707 0.02818 0.01659 -0.1300 0.6313 0.5597
1.750 0.6974 0.02831 0.01674 -0.1297 0.6229 0.5752
2.000 0.7233 0.02850 0.01697 -0.1293 0.6149 0.5919
2.250 0.7483 0.02870 0.01722 -0.1288 0.6065 0.6106
2.500 0.7745 0.02885 0.01743 -0.1284 0.5991 0.6306
2.750 0.7951 0.02917 0.01788 -0.1272 0.5907 0.6522
3.000 0.8258 0.02913 0.01788 -0.1272 0.5848 0.6808
3.250 0.8381 0.02969 0.01864 -0.1248 0.5757 0.7088
3.500 0.8640 0.02960 0.01867 -0.1239 0.5699 0.7505
3.750 0.8717 0.03006 0.01936 -0.1204 0.5619 0.8044
4.000 0.8917 0.02998 0.01942 -0.1186 0.5552 1.0000
4.250 0.9206 0.03058 0.01991 -0.1195 0.5483 1.0000
4.500 0.9430 0.03136 0.02063 -0.1193 0.5406 1.0000
4.750 0.9802 0.03155 0.02067 -0.1207 0.5355 1.0000
5.000 0.9894 0.03283 0.02201 -0.1187 0.5268 1.0000
5.250 1.0194 0.03324 0.02237 -0.1192 0.5210 1.0000
5.500 1.0379 0.03416 0.02330 -0.1182 0.5143 1.0000
5.750 1.0548 0.03513 0.02430 -0.1171 0.5072 1.0000
6.000 1.0905 0.03530 0.02440 -0.1181 0.5024 1.0000
6.250 1.0901 0.03705 0.02628 -0.1149 0.4941 1.0000
6.500 1.1151 0.03766 0.02689 -0.1147 0.4885 1.0000
6.750 1.1395 0.03833 0.02757 -0.1144 0.4831 1.0000
7.000 1.1347 0.04028 0.02966 -0.1108 0.4750 1.0000
7.250 1.1687 0.04049 0.02986 -0.1115 0.4703 1.0000
7.500 1.1559 0.04289 0.03238 -0.1072 0.4626 1.0000
7.750 1.1684 0.04410 0.03366 -0.1057 0.4563 1.0000
8.000 1.2131 0.04368 0.03324 -0.1073 0.4524 1.0000
8.250 1.1602 0.04878 0.03853 -0.1004 0.4418 1.0000
8.500 1.1962 0.04856 0.03834 -0.1007 0.4376 1.0000
8.750 1.1407 0.05512 0.04505 -0.0960 0.4259 1.0000
9.000 1.1713 0.05506 0.04504 -0.0957 0.4217 1.0000
9.250 1.2237 0.05332 0.04335 -0.0964 0.4192 1.0000
9.500 1.1488 0.06265 0.05280 -0.0929 0.4048 1.0000
9.750 1.1951 0.06081 0.05104 -0.0926 0.4028 1.0000
11.500 1.1081 0.09463 0.08547 -0.0926 0.3368 1.0000
11.750 1.0882 0.10116 0.09208 -0.0940 0.3253 1.0000
12.000 1.1192 0.10006 0.09110 -0.0926 0.3225 1.0000
12.250 1.0909 0.10799 0.09909 -0.0948 0.3096 1.0000
12.500 1.1209 0.10696 0.09817 -0.0934 0.3068 1.0000
13.000 1.1183 0.11460 0.10599 -0.0948 0.2902 1.0000
13.250 1.0989 0.12151 0.11297 -0.0971 0.2787 1.0000
13.500 1.1292 0.12007 0.11166 -0.0955 0.2756 1.0000
13.750 1.1052 0.12795 0.11960 -0.0986 0.2634 1.0000
14.000 1.1302 0.12734 0.11911 -0.0973 0.2597 1.0000
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Polar data table (+)
Polar graphs
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