EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Reynolds number: 200,000 Max Cl/Cd: 56.39 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e818-il-200000.txt Download as CSV file: xf-e818-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4988 0.09418 0.09098 -0.0350 1.0000 0.0406
-8.500 -0.5101 0.09103 0.08788 -0.0346 1.0000 0.0414
-8.250 -0.5233 0.08772 0.08463 -0.0343 1.0000 0.0422
-8.000 -0.5382 0.08436 0.08133 -0.0340 1.0000 0.0426
-7.750 -0.5566 0.08091 0.07795 -0.0336 1.0000 0.0427
-7.500 -0.5777 0.07763 0.07473 -0.0328 1.0000 0.0424
-7.250 -0.5953 0.07156 0.06867 -0.0375 1.0000 0.0418
-6.250 -0.6034 0.04938 0.04552 -0.0528 1.0000 0.0487
-6.000 -0.5884 0.04639 0.04244 -0.0535 1.0000 0.0523
-5.000 -0.4465 0.02816 0.02149 -0.0637 0.9947 0.0227
-4.750 -0.4132 0.02519 0.01830 -0.0649 0.9938 0.0184
-4.500 -0.3806 0.02285 0.01556 -0.0656 0.9927 0.0161
-4.250 -0.3490 0.02110 0.01362 -0.0661 0.9912 0.0146
-4.000 -0.3164 0.01969 0.01210 -0.0671 0.9896 0.0137
-3.750 -0.2820 0.01858 0.01084 -0.0687 0.9880 0.0134
-3.500 -0.2472 0.01784 0.00986 -0.0705 0.9863 0.0139
-3.250 -0.2121 0.01738 0.00912 -0.0721 0.9845 0.0161
-3.000 -0.1730 0.01554 0.00837 -0.0759 0.9839 0.2801
-2.750 -0.1390 0.01537 0.00876 -0.0778 0.9824 0.4378
-2.500 -0.1086 0.01572 0.00924 -0.0785 0.9800 0.5064
-2.250 -0.0823 0.01573 0.00918 -0.0785 0.9768 0.5273
-2.000 -0.0524 0.01584 0.00927 -0.0793 0.9738 0.5465
-1.750 -0.0205 0.01600 0.00945 -0.0804 0.9713 0.5646
-1.500 0.0144 0.01626 0.00970 -0.0822 0.9691 0.5845
-1.250 0.0399 0.01631 0.00980 -0.0820 0.9653 0.6014
-1.000 0.0683 0.01642 0.00995 -0.0825 0.9616 0.6193
-0.750 0.1012 0.01660 0.01012 -0.0838 0.9586 0.6388
-0.500 0.1364 0.01684 0.01043 -0.0855 0.9563 0.6575
-0.250 0.1599 0.01691 0.01056 -0.0850 0.9513 0.6761
0.000 0.1900 0.01703 0.01077 -0.0857 0.9473 0.6952
0.250 0.2255 0.01721 0.01103 -0.0874 0.9444 0.7160
0.500 0.2520 0.01732 0.01125 -0.0874 0.9393 0.7352
0.750 0.2821 0.01740 0.01142 -0.0880 0.9343 0.7565
1.000 0.3184 0.01750 0.01165 -0.0897 0.9312 0.7777
1.250 0.3413 0.01757 0.01185 -0.0889 0.9246 0.7998
1.500 0.3736 0.01759 0.01201 -0.0897 0.9201 0.8242
1.750 0.4120 0.01756 0.01216 -0.0916 0.9172 0.8505
2.000 0.4289 0.01746 0.01234 -0.0892 0.9080 0.8831
2.250 0.4673 0.01718 0.01228 -0.0907 0.9046 0.9343
2.500 0.5009 0.01703 0.01226 -0.0922 0.8953 1.0000
2.750 0.5564 0.01661 0.01201 -0.0972 0.8916 1.0000
3.000 0.5983 0.01606 0.01163 -0.0993 0.8808 1.0000
3.250 0.6795 0.01205 0.00514 -0.0992 0.2995 1.0000
3.500 0.6801 0.01522 0.00686 -0.0948 0.0266 1.0000
3.750 0.7031 0.01621 0.00801 -0.0937 0.0231 1.0000
4.000 0.7244 0.01745 0.00932 -0.0923 0.0218 1.0000
4.250 0.7476 0.01898 0.01089 -0.0911 0.0213 1.0000
4.500 0.7772 0.02096 0.01292 -0.0908 0.0213 1.0000
4.750 0.8085 0.02425 0.01628 -0.0917 0.0148 1.0000
5.000 0.8375 0.02557 0.01782 -0.0912 0.0136 1.0000
5.250 0.8679 0.02897 0.02157 -0.0907 0.0141 1.0000
5.500 0.8978 0.03106 0.02385 -0.0900 0.0167 1.0000
6.500 0.9803 0.04784 0.04261 -0.0792 0.0350 1.0000
6.750 0.9917 0.05096 0.04617 -0.0766 0.0323 1.0000
7.000 1.0009 0.05432 0.04976 -0.0744 0.0304 1.0000
7.250 1.0087 0.05799 0.05355 -0.0727 0.0290 1.0000
7.500 1.0157 0.06330 0.05887 -0.0718 0.0279 1.0000
7.750 1.0026 0.07249 0.06827 -0.0696 0.0269 1.0000
8.000 0.9998 0.07588 0.07193 -0.0667 0.0269 1.0000
8.250 0.9938 0.07910 0.07540 -0.0639 0.0268 1.0000
8.500 0.9844 0.08211 0.07864 -0.0610 0.0266 1.0000
8.750 0.9700 0.08484 0.08155 -0.0578 0.0265 1.0000
9.000 0.9533 0.08791 0.08476 -0.0552 0.0263 1.0000
9.250 0.9364 0.09170 0.08867 -0.0541 0.0263 1.0000
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Polar data table (+)
Polar graphs
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