EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Reynolds number: 200,000 Max Cl/Cd: 67.27 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e818-il-200000-n5.txt Download as CSV file: xf-e818-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 818 HYDROFOIL AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4673 0.10077 0.09728 -0.0384 1.0000 0.0091
-9.500 -0.4751 0.09728 0.09385 -0.0380 1.0000 0.0088
-9.250 -0.4780 0.09282 0.08943 -0.0398 0.9991 0.0086
-9.000 -0.4746 0.08682 0.08345 -0.0446 0.9967 0.0083
-8.750 -0.4711 0.08037 0.07702 -0.0501 0.9939 0.0081
-8.500 -0.4708 0.07261 0.06927 -0.0566 0.9900 0.0079
-8.250 -0.4729 0.06381 0.06040 -0.0665 0.9846 0.0079
-8.000 -0.4793 0.05714 0.05359 -0.0756 0.9769 0.0079
-7.750 -0.4754 0.05027 0.04641 -0.0858 0.9699 0.0077
-7.500 -0.4713 0.04552 0.04136 -0.0894 0.9632 0.0075
-7.250 -0.4583 0.04066 0.03610 -0.0929 0.9589 0.0071
-7.000 -0.4374 0.03608 0.03103 -0.0961 0.9565 0.0066
-6.750 -0.4213 0.03257 0.02708 -0.0965 0.9524 0.0062
-6.500 -0.3995 0.02932 0.02336 -0.0971 0.9491 0.0058
-6.250 -0.3725 0.02628 0.01983 -0.0979 0.9470 0.0054
-6.000 -0.3436 0.02393 0.01711 -0.0987 0.9455 0.0051
-5.750 -0.3141 0.02192 0.01480 -0.0994 0.9444 0.0048
-5.500 -0.2841 0.02030 0.01298 -0.1002 0.9435 0.0047
-5.250 -0.2612 0.01906 0.01151 -0.0997 0.9407 0.0046
-5.000 -0.2365 0.01795 0.01027 -0.0996 0.9378 0.0046
-4.750 -0.2070 0.01691 0.00905 -0.1006 0.9359 0.0046
-4.500 -0.1758 0.01609 0.00800 -0.1017 0.9344 0.0048
-4.250 -0.1441 0.01550 0.00716 -0.1028 0.9332 0.0051
-4.000 -0.1121 0.01507 0.00650 -0.1039 0.9322 0.0059
-3.750 -0.0794 0.01473 0.00601 -0.1050 0.9312 0.0085
-3.500 -0.0454 0.01280 0.00542 -0.1084 0.9308 0.3071
-3.250 -0.0177 0.01250 0.00553 -0.1090 0.9287 0.4148
-3.000 0.0050 0.01251 0.00543 -0.1082 0.9253 0.4301
-2.750 0.0333 0.01248 0.00537 -0.1085 0.9232 0.4450
-2.500 0.0635 0.01244 0.00531 -0.1092 0.9215 0.4601
-2.250 0.0946 0.01239 0.00526 -0.1100 0.9202 0.4754
-2.000 0.1266 0.01235 0.00522 -0.1111 0.9190 0.4908
-1.750 0.1593 0.01230 0.00516 -0.1123 0.9180 0.5062
-1.500 0.1923 0.01225 0.00514 -0.1135 0.9172 0.5215
-1.250 0.2083 0.01241 0.00533 -0.1113 0.9117 0.5348
-1.000 0.2374 0.01241 0.00538 -0.1118 0.9095 0.5500
-0.750 0.2686 0.01238 0.00542 -0.1126 0.9078 0.5659
-0.500 0.3009 0.01235 0.00545 -0.1137 0.9064 0.5822
-0.250 0.3341 0.01231 0.00548 -0.1149 0.9052 0.5985
0.000 0.3609 0.01235 0.00561 -0.1148 0.9023 0.6136
0.250 0.3839 0.01243 0.00578 -0.1140 0.8977 0.6284
0.500 0.4148 0.01240 0.00586 -0.1147 0.8953 0.6443
0.750 0.4475 0.01233 0.00591 -0.1157 0.8934 0.6605
1.000 0.4819 0.01224 0.00594 -0.1170 0.8918 0.6769
1.250 0.5026 0.01233 0.00629 -0.1156 0.8854 0.6923
1.500 0.5343 0.01222 0.00635 -0.1162 0.8818 0.7087
1.750 0.5700 0.01202 0.00633 -0.1176 0.8791 0.7257
2.000 0.5935 0.01199 0.00648 -0.1165 0.8715 0.7426
2.250 0.6315 0.01160 0.00631 -0.1180 0.8660 0.7598
2.500 0.6604 0.01125 0.00617 -0.1175 0.8539 0.7772
2.750 0.6888 0.01024 0.00531 -0.1155 0.7982 0.7950
3.000 0.6794 0.01252 0.00500 -0.1067 0.3023 0.8118
3.250 0.6781 0.01495 0.00601 -0.1020 0.0254 0.8320
3.500 0.6963 0.01559 0.00678 -0.0996 0.0124 0.8557
3.750 0.7136 0.01611 0.00754 -0.0971 0.0106 0.8854
4.000 0.7288 0.01667 0.00831 -0.0942 0.0097 0.9365
4.250 0.7508 0.01765 0.00942 -0.0930 0.0091 1.0000
4.500 0.7726 0.01894 0.01078 -0.0918 0.0086 1.0000
4.750 0.7959 0.02046 0.01235 -0.0910 0.0072 1.0000
5.000 0.8220 0.02200 0.01400 -0.0908 0.0050 1.0000
5.250 0.8499 0.02350 0.01565 -0.0906 0.0041 1.0000
5.500 0.8794 0.02576 0.01816 -0.0903 0.0038 1.0000
5.750 0.9077 0.02841 0.02116 -0.0897 0.0036 1.0000
6.000 0.9328 0.03144 0.02472 -0.0885 0.0035 1.0000
6.250 0.9542 0.03481 0.02852 -0.0866 0.0035 1.0000
6.500 0.9717 0.03852 0.03268 -0.0842 0.0035 1.0000
6.750 0.9856 0.04245 0.03703 -0.0815 0.0037 1.0000
7.000 0.9961 0.04654 0.04150 -0.0786 0.0038 1.0000
7.250 1.0032 0.05069 0.04601 -0.0755 0.0039 1.0000
7.500 1.0070 0.05493 0.05057 -0.0724 0.0041 1.0000
7.750 1.0076 0.05914 0.05506 -0.0694 0.0043 1.0000
8.000 1.0046 0.06332 0.05950 -0.0664 0.0044 1.0000
8.250 0.9978 0.06743 0.06383 -0.0634 0.0045 1.0000
8.500 0.9859 0.07115 0.06773 -0.0601 0.0046 1.0000
8.750 0.9706 0.07481 0.07153 -0.0571 0.0047 1.0000
9.000 0.9541 0.07879 0.07565 -0.0552 0.0047 1.0000
9.250 0.9369 0.08329 0.08027 -0.0545 0.0048 1.0000
9.500 0.9196 0.08847 0.08557 -0.0554 0.0048 1.0000
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Polar data table (+)
Polar graphs
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