EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Reynolds number: 200,000 Max Cl/Cd: 71.35 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e817-il-200000-n5.txt Download as CSV file: xf-e817-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 817 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5363 0.08600 0.08258 -0.0519 0.9986 0.0048
-10.750 -0.5470 0.07674 0.07323 -0.0595 0.9960 0.0047
-10.500 -0.5585 0.06787 0.06422 -0.0679 0.9928 0.0047
-10.250 -0.5710 0.05983 0.05599 -0.0760 0.9879 0.0046
-10.000 -0.5749 0.05363 0.04959 -0.0836 0.9833 0.0046
-9.750 -0.5827 0.04805 0.04376 -0.0897 0.9764 0.0046
-9.500 -0.5862 0.04354 0.03897 -0.0949 0.9698 0.0045
-9.250 -0.5889 0.03998 0.03512 -0.0970 0.9619 0.0045
-9.000 -0.5799 0.03620 0.03093 -0.0995 0.9577 0.0045
-8.750 -0.5675 0.03315 0.02750 -0.1006 0.9539 0.0046
-8.500 -0.5560 0.03079 0.02476 -0.1002 0.9489 0.0046
-8.250 -0.5365 0.02840 0.02205 -0.1009 0.9463 0.0047
-8.000 -0.5133 0.02629 0.01966 -0.1017 0.9445 0.0048
-7.750 -0.4880 0.02447 0.01760 -0.1028 0.9432 0.0049
-7.500 -0.4745 0.02330 0.01626 -0.1011 0.9388 0.0051
-7.250 -0.4552 0.02149 0.01425 -0.1011 0.9356 0.0054
-7.000 -0.4298 0.01990 0.01246 -0.1021 0.9336 0.0066
-6.750 -0.4008 0.01896 0.01136 -0.1033 0.9322 0.0079
-6.500 -0.3709 0.01816 0.01043 -0.1047 0.9311 0.0121
-6.250 -0.3402 0.01696 0.00917 -0.1062 0.9302 0.0257
-6.000 -0.3216 0.01609 0.00851 -0.1055 0.9268 0.0663
-5.750 -0.2985 0.01496 0.00778 -0.1061 0.9241 0.1467
-5.500 -0.2704 0.01425 0.00732 -0.1071 0.9223 0.2365
-5.250 -0.2404 0.01398 0.00707 -0.1081 0.9209 0.2776
-5.000 -0.2098 0.01381 0.00685 -0.1090 0.9197 0.3038
-4.750 -0.1788 0.01366 0.00667 -0.1099 0.9188 0.3266
-4.500 -0.1474 0.01355 0.00652 -0.1110 0.9179 0.3514
-4.250 -0.1156 0.01346 0.00639 -0.1121 0.9171 0.3732
-4.000 -0.0949 0.01348 0.00638 -0.1109 0.9137 0.3846
-3.750 -0.0715 0.01347 0.00630 -0.1102 0.9108 0.3947
-3.500 -0.0437 0.01344 0.00621 -0.1104 0.9091 0.4053
-3.250 -0.0137 0.01339 0.00612 -0.1111 0.9076 0.4166
-3.000 0.0173 0.01332 0.00603 -0.1119 0.9064 0.4275
-2.750 0.0486 0.01326 0.00597 -0.1129 0.9054 0.4388
-2.500 0.0801 0.01321 0.00588 -0.1138 0.9045 0.4504
-2.250 0.1124 0.01315 0.00583 -0.1149 0.9036 0.4620
-2.000 0.1265 0.01335 0.00604 -0.1124 0.8984 0.4721
-1.750 0.1537 0.01337 0.00608 -0.1125 0.8961 0.4841
-1.500 0.1836 0.01336 0.00608 -0.1131 0.8944 0.4959
-1.250 0.2149 0.01333 0.00609 -0.1139 0.8930 0.5083
-1.000 0.2468 0.01329 0.00610 -0.1149 0.8919 0.5210
-0.750 0.2795 0.01325 0.00610 -0.1160 0.8908 0.5336
-0.500 0.2969 0.01344 0.00636 -0.1141 0.8858 0.5449
-0.250 0.3234 0.01349 0.00648 -0.1140 0.8829 0.5574
0.000 0.3539 0.01347 0.00653 -0.1146 0.8809 0.5704
0.250 0.3862 0.01342 0.00656 -0.1156 0.8793 0.5839
0.500 0.4197 0.01335 0.00658 -0.1167 0.8779 0.5976
1.000 0.4676 0.01350 0.00695 -0.1153 0.8690 0.6235
1.250 0.5010 0.01337 0.00694 -0.1163 0.8666 0.6377
1.500 0.5367 0.01319 0.00689 -0.1178 0.8647 0.6522
1.750 0.5568 0.01327 0.00714 -0.1162 0.8576 0.6655
2.000 0.5910 0.01303 0.00703 -0.1172 0.8535 0.6801
2.250 0.6231 0.01279 0.00694 -0.1176 0.8481 0.6946
2.500 0.6542 0.01245 0.00675 -0.1178 0.8396 0.7095
2.750 0.6833 0.01204 0.00648 -0.1173 0.8270 0.7245
3.000 0.7091 0.01158 0.00614 -0.1160 0.8068 0.7396
3.250 0.7315 0.01128 0.00603 -0.1142 0.7810 0.7550
3.500 0.7539 0.01102 0.00587 -0.1124 0.7410 0.7707
3.750 0.7884 0.01105 0.00516 -0.1123 0.5824 0.7861
4.000 0.7928 0.01210 0.00563 -0.1075 0.4604 0.8030
4.250 0.7947 0.01328 0.00624 -0.1027 0.3386 0.8218
4.500 0.7985 0.01449 0.00689 -0.0984 0.2181 0.8430
4.750 0.8072 0.01547 0.00749 -0.0950 0.1313 0.8687
5.000 0.8162 0.01626 0.00803 -0.0916 0.0764 0.9063
5.250 0.8316 0.01694 0.00856 -0.0894 0.0409 1.0000
5.500 0.8508 0.01784 0.00930 -0.0882 0.0188 1.0000
5.750 0.8704 0.01878 0.01029 -0.0868 0.0120 1.0000
6.000 0.8903 0.01968 0.01137 -0.0855 0.0099 1.0000
6.250 0.9084 0.02085 0.01264 -0.0839 0.0086 1.0000
6.500 0.9254 0.02246 0.01437 -0.0821 0.0079 1.0000
6.750 0.9469 0.02439 0.01643 -0.0811 0.0075 1.0000
7.000 0.9737 0.02615 0.01835 -0.0810 0.0073 1.0000
7.250 1.0025 0.02827 0.02069 -0.0812 0.0072 1.0000
7.500 1.0295 0.03068 0.02338 -0.0810 0.0071 1.0000
7.750 1.0530 0.03338 0.02642 -0.0803 0.0070 1.0000
8.000 1.0720 0.03612 0.02954 -0.0788 0.0068 1.0000
8.250 1.0879 0.03834 0.03208 -0.0770 0.0063 1.0000
8.500 1.1011 0.04049 0.03454 -0.0749 0.0056 1.0000
8.750 1.1112 0.04261 0.03694 -0.0726 0.0050 1.0000
9.000 1.1179 0.04476 0.03934 -0.0700 0.0046 1.0000
9.250 1.1173 0.04767 0.04257 -0.0663 0.0045 1.0000
9.500 1.1110 0.05095 0.04617 -0.0622 0.0044 1.0000
9.750 1.1011 0.05432 0.04983 -0.0581 0.0044 1.0000
10.000 1.0878 0.05797 0.05384 -0.0543 0.0043 1.0000
10.250 1.0713 0.06210 0.05823 -0.0511 0.0043 1.0000
10.500 1.0531 0.06650 0.06287 -0.0486 0.0043 1.0000
10.750 1.0309 0.07185 0.06839 -0.0471 0.0044 1.0000
11.000 1.0068 0.07793 0.07470 -0.0470 0.0044 1.0000
11.250 0.9810 0.08508 0.08204 -0.0487 0.0045 1.0000
11.500 0.9549 0.09371 0.09084 -0.0529 0.0047 1.0000
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Polar data table (+)
Polar graphs
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