EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Reynolds number: 100,000 Max Cl/Cd: 40.94 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e818-il-100000-n5.txt Download as CSV file: xf-e818-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4775 0.08822 0.08341 -0.0428 1.0000 0.0102
-8.750 -0.4881 0.08424 0.07949 -0.0429 1.0000 0.0100
-8.500 -0.5008 0.08006 0.07537 -0.0431 1.0000 0.0099
-8.250 -0.5160 0.07596 0.07131 -0.0435 1.0000 0.0099
-8.000 -0.5337 0.07228 0.06766 -0.0436 1.0000 0.0098
-7.750 -0.5557 0.06912 0.06453 -0.0431 1.0000 0.0098
-7.500 -0.5743 0.06543 0.06080 -0.0445 1.0000 0.0098
-7.250 -0.5735 0.05926 0.05439 -0.0518 0.9960 0.0097
-7.000 -0.5649 0.05350 0.04828 -0.0577 0.9918 0.0095
-6.750 -0.5530 0.04843 0.04279 -0.0616 0.9881 0.0093
-6.500 -0.5343 0.04375 0.03764 -0.0652 0.9850 0.0091
-6.250 -0.5104 0.03943 0.03277 -0.0683 0.9827 0.0089
-6.000 -0.4835 0.03589 0.02869 -0.0706 0.9811 0.0088
-5.750 -0.4591 0.03287 0.02518 -0.0715 0.9792 0.0087
-5.500 -0.4327 0.03034 0.02225 -0.0721 0.9774 0.0086
-5.250 -0.4052 0.02818 0.01975 -0.0726 0.9756 0.0085
-5.000 -0.3771 0.02633 0.01766 -0.0730 0.9741 0.0086
-4.750 -0.3487 0.02476 0.01590 -0.0735 0.9727 0.0087
-4.500 -0.3183 0.02340 0.01418 -0.0746 0.9713 0.0090
-4.250 -0.2858 0.02230 0.01277 -0.0762 0.9700 0.0094
-4.000 -0.2522 0.02142 0.01153 -0.0778 0.9688 0.0102
-3.750 -0.2222 0.02048 0.01034 -0.0787 0.9670 0.0167
-3.500 -0.1883 0.01796 0.01002 -0.0826 0.9668 0.4189
-3.250 -0.1612 0.01795 0.00983 -0.0825 0.9641 0.4499
-3.000 -0.1326 0.01792 0.00963 -0.0829 0.9617 0.4676
-2.750 -0.1032 0.01793 0.00952 -0.0834 0.9595 0.4845
-2.500 -0.0726 0.01796 0.00933 -0.0842 0.9575 0.5026
-2.250 -0.0411 0.01803 0.00932 -0.0852 0.9558 0.5206
-2.000 -0.0174 0.01804 0.00931 -0.0847 0.9524 0.5366
-1.750 0.0097 0.01809 0.00934 -0.0848 0.9494 0.5540
-1.250 0.0697 0.01826 0.00951 -0.0862 0.9445 0.5896
-1.000 0.0991 0.01837 0.00957 -0.0868 0.9421 0.6077
-0.750 0.1230 0.01845 0.00967 -0.0863 0.9379 0.6255
-0.500 0.1511 0.01854 0.00982 -0.0865 0.9347 0.6431
-0.250 0.1820 0.01865 0.00998 -0.0874 0.9320 0.6624
0.000 0.2119 0.01876 0.01016 -0.0880 0.9291 0.6811
0.250 0.2348 0.01887 0.01034 -0.0872 0.9242 0.6994
0.500 0.2641 0.01897 0.01053 -0.0877 0.9206 0.7193
0.750 0.2959 0.01906 0.01073 -0.0886 0.9179 0.7397
1.000 0.3179 0.01917 0.01095 -0.0876 0.9123 0.7603
1.250 0.3457 0.01924 0.01115 -0.0876 0.9078 0.7828
1.750 0.3966 0.01931 0.01155 -0.0866 0.8973 0.8333
2.000 0.4257 0.01925 0.01184 -0.0866 0.8929 0.8655
2.250 0.4469 0.01919 0.01200 -0.0852 0.8858 0.9157
2.500 0.4838 0.01908 0.01209 -0.0871 0.8804 1.0000
2.750 0.5146 0.01919 0.01234 -0.0879 0.8728 1.0000
3.750 0.6866 0.01677 0.00776 -0.0899 0.1823 1.0000
4.000 0.6999 0.01935 0.00921 -0.0878 0.0245 1.0000
4.250 0.7222 0.02043 0.01047 -0.0866 0.0184 1.0000
4.500 0.7417 0.02185 0.01205 -0.0850 0.0162 1.0000
4.750 0.7605 0.02389 0.01418 -0.0833 0.0150 1.0000
5.000 0.7873 0.02570 0.01610 -0.0828 0.0144 1.0000
5.250 0.8189 0.02792 0.01848 -0.0830 0.0138 1.0000
5.500 0.8516 0.03056 0.02138 -0.0831 0.0134 1.0000
5.750 0.8814 0.03352 0.02471 -0.0826 0.0132 1.0000
6.000 0.9069 0.03636 0.02798 -0.0814 0.0125 1.0000
6.250 0.9289 0.03884 0.03090 -0.0799 0.0106 1.0000
6.500 0.9462 0.04078 0.03330 -0.0786 0.0082 1.0000
6.750 0.9589 0.04330 0.03611 -0.0769 0.0071 1.0000
7.000 0.9699 0.04687 0.04009 -0.0746 0.0068 1.0000
7.250 0.9794 0.05048 0.04411 -0.0720 0.0069 1.0000
7.500 0.9859 0.05423 0.04826 -0.0691 0.0070 1.0000
7.750 0.9896 0.05813 0.05253 -0.0662 0.0071 1.0000
8.000 0.9898 0.06223 0.05696 -0.0632 0.0073 1.0000
8.250 0.9855 0.06652 0.06157 -0.0601 0.0076 1.0000
8.500 0.9758 0.07072 0.06603 -0.0569 0.0078 1.0000
8.750 0.9619 0.07470 0.07021 -0.0539 0.0080 1.0000
9.000 0.9463 0.07887 0.07455 -0.0519 0.0082 1.0000
9.250 0.9296 0.08343 0.07926 -0.0511 0.0083 1.0000
9.500 0.9125 0.08860 0.08456 -0.0517 0.0085 1.0000
9.750 0.8962 0.09455 0.09060 -0.0540 0.0086 1.0000
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Polar data table (+)
Polar graphs
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