EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Reynolds number: 500,000 Max Cl/Cd: 104.16 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e818-il-500000.txt Download as CSV file: xf-e818-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4612 0.11690 0.11463 -0.0367 1.0000 0.0109
-10.750 -0.4669 0.11308 0.11084 -0.0366 1.0000 0.0112
-10.500 -0.4731 0.10977 0.10757 -0.0360 1.0000 0.0114
-10.250 -0.4798 0.10676 0.10459 -0.0352 1.0000 0.0116
-10.000 -0.4872 0.10415 0.10202 -0.0340 1.0000 0.0119
-9.750 -0.4808 0.09956 0.09742 -0.0374 0.9989 0.0121
-9.500 -0.4729 0.09493 0.09280 -0.0412 0.9975 0.0125
-9.250 -0.4656 0.08983 0.08771 -0.0457 0.9957 0.0129
-9.000 -0.4585 0.08436 0.08225 -0.0509 0.9941 0.0133
-8.750 -0.4539 0.07859 0.07648 -0.0562 0.9916 0.0136
-8.500 -0.4531 0.06981 0.06772 -0.0644 0.9878 0.0134
-8.250 -0.4589 0.05655 0.05428 -0.0834 0.9823 0.0128
-8.000 -0.4580 0.05024 0.04776 -0.0936 0.9738 0.0129
-7.750 -0.4446 0.04505 0.04232 -0.1005 0.9704 0.0134
-5.250 -0.1978 0.01687 0.01115 -0.1141 0.9469 0.0108
-5.000 -0.1667 0.01441 0.00859 -0.1151 0.9461 0.0084
-4.750 -0.1327 0.01293 0.00694 -0.1167 0.9454 0.0073
-4.500 -0.0979 0.01192 0.00572 -0.1184 0.9448 0.0066
-4.250 -0.0638 0.01133 0.00494 -0.1199 0.9442 0.0064
-4.000 -0.0301 0.01099 0.00443 -0.1212 0.9436 0.0067
-3.750 -0.0046 0.01087 0.00418 -0.1208 0.9410 0.0081
-3.500 0.0209 0.00967 0.00372 -0.1215 0.9381 0.2048
-3.250 0.0508 0.00912 0.00356 -0.1227 0.9365 0.3240
-3.000 0.0815 0.00897 0.00349 -0.1236 0.9352 0.3589
-2.750 0.1131 0.00872 0.00351 -0.1248 0.9341 0.4297
-2.500 0.1451 0.00861 0.00353 -0.1259 0.9331 0.4726
-2.250 0.1775 0.00853 0.00348 -0.1270 0.9321 0.4878
-2.000 0.2100 0.00846 0.00341 -0.1282 0.9312 0.5029
-1.750 0.2425 0.00840 0.00337 -0.1293 0.9304 0.5178
-1.500 0.2630 0.00850 0.00352 -0.1280 0.9262 0.5312
-1.250 0.2908 0.00850 0.00356 -0.1282 0.9238 0.5459
-1.000 0.3212 0.00845 0.00357 -0.1288 0.9220 0.5602
-0.750 0.3529 0.00838 0.00356 -0.1298 0.9206 0.5749
-0.500 0.3854 0.00829 0.00352 -0.1308 0.9192 0.5898
-0.250 0.4182 0.00820 0.00350 -0.1319 0.9178 0.6047
0.000 0.4426 0.00826 0.00362 -0.1313 0.9140 0.6192
0.250 0.4708 0.00821 0.00365 -0.1314 0.9103 0.6341
0.500 0.5029 0.00807 0.00360 -0.1323 0.9075 0.6495
0.750 0.5365 0.00791 0.00359 -0.1333 0.9050 0.6649
1.000 0.5619 0.00787 0.00366 -0.1327 0.8991 0.6793
1.250 0.5931 0.00766 0.00356 -0.1332 0.8938 0.6942
1.500 0.6214 0.00741 0.00340 -0.1328 0.8839 0.7092
1.750 0.6509 0.00699 0.00302 -0.1322 0.8664 0.7243
2.000 0.6742 0.00669 0.00275 -0.1304 0.8374 0.7395
2.250 0.6906 0.00663 0.00242 -0.1270 0.7342 0.7550
2.500 0.6701 0.00951 0.00328 -0.1174 0.3135 0.7696
2.750 0.6735 0.01184 0.00432 -0.1131 0.0137 0.7853
3.000 0.6968 0.01227 0.00496 -0.1119 0.0115 0.8032
3.250 0.7187 0.01287 0.00574 -0.1104 0.0110 0.8225
3.500 0.7401 0.01336 0.00634 -0.1090 0.0088 0.8428
3.750 0.7547 0.01473 0.00789 -0.1062 0.0065 0.8655
4.000 0.7720 0.01563 0.00895 -0.1037 0.0059 0.8930
4.250 0.7855 0.01626 0.00974 -0.1003 0.0054 0.9418
4.500 0.8120 0.01787 0.01148 -0.0996 0.0051 1.0000
4.750 0.8428 0.02044 0.01424 -0.0994 0.0053 1.0000
5.000 0.8735 0.02273 0.01665 -0.0992 0.0070 1.0000
5.500 0.9203 0.03497 0.02997 -0.0943 0.0147 1.0000
5.750 0.9497 0.03396 0.02910 -0.0932 0.0121 1.0000
6.000 0.9690 0.03658 0.03201 -0.0911 0.0107 1.0000
6.250 0.9854 0.03946 0.03523 -0.0889 0.0096 1.0000
6.500 0.9990 0.04245 0.03847 -0.0867 0.0088 1.0000
6.750 1.0103 0.04545 0.04170 -0.0844 0.0082 1.0000
7.000 1.0192 0.04847 0.04491 -0.0822 0.0078 1.0000
7.250 1.0252 0.05170 0.04833 -0.0799 0.0074 1.0000
7.500 1.0263 0.05551 0.05235 -0.0771 0.0070 1.0000
7.750 1.0217 0.05997 0.05703 -0.0741 0.0068 1.0000
8.000 1.0108 0.06504 0.06233 -0.0707 0.0066 1.0000
8.250 0.9951 0.07020 0.06768 -0.0672 0.0064 1.0000
8.500 0.9761 0.07417 0.07180 -0.0632 0.0064 1.0000
8.750 0.9576 0.07792 0.07568 -0.0602 0.0063 1.0000
9.000 0.9404 0.08189 0.07977 -0.0585 0.0063 1.0000
9.250 0.9254 0.08606 0.08405 -0.0580 0.0063 1.0000
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Polar data table (+)
Polar graphs
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