EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Reynolds number: 100,000 Max Cl/Cd: 47.25 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e817-il-100000-n5.txt Download as CSV file: xf-e817-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5067 0.09588 0.09095 -0.0501 1.0000 0.0107
-10.750 -0.5209 0.09085 0.08598 -0.0508 1.0000 0.0102
-10.500 -0.5390 0.08506 0.08021 -0.0523 1.0000 0.0101
-10.250 -0.5608 0.07919 0.07445 -0.0540 1.0000 0.0100
-10.000 -0.5789 0.07481 0.07007 -0.0549 1.0000 0.0098
-9.750 -0.6016 0.07018 0.06541 -0.0558 1.0000 0.0097
-9.500 -0.6236 0.06631 0.06151 -0.0562 1.0000 0.0096
-9.250 -0.6462 0.06305 0.05821 -0.0558 1.0000 0.0095
-9.000 -0.6609 0.05817 0.05314 -0.0604 0.9950 0.0095
-8.750 -0.6681 0.05340 0.04807 -0.0649 0.9896 0.0095
-8.500 -0.6659 0.04896 0.04324 -0.0680 0.9848 0.0094
-8.250 -0.6550 0.04459 0.03839 -0.0710 0.9814 0.0095
-8.000 -0.6458 0.04126 0.03465 -0.0714 0.9777 0.0098
-7.750 -0.6299 0.03866 0.03153 -0.0718 0.9749 0.0104
-7.500 -0.6129 0.03534 0.02780 -0.0727 0.9725 0.0117
-7.250 -0.5909 0.03310 0.02533 -0.0738 0.9705 0.0132
-7.000 -0.5654 0.03131 0.02331 -0.0748 0.9689 0.0156
-6.750 -0.5452 0.02956 0.02136 -0.0742 0.9668 0.0165
-6.500 -0.5244 0.02794 0.01955 -0.0737 0.9647 0.0182
-6.250 -0.5006 0.02654 0.01791 -0.0739 0.9626 0.0202
-6.000 -0.4743 0.02498 0.01624 -0.0751 0.9607 0.0295
-5.750 -0.4450 0.02324 0.01445 -0.0769 0.9592 0.0510
-5.500 -0.4149 0.02124 0.01285 -0.0794 0.9581 0.1226
-5.250 -0.3848 0.02009 0.01230 -0.0816 0.9571 0.2584
-5.000 -0.3537 0.01994 0.01200 -0.0828 0.9558 0.3121
-4.750 -0.3301 0.01985 0.01183 -0.0824 0.9531 0.3424
-4.500 -0.3040 0.01985 0.01172 -0.0824 0.9507 0.3718
-4.250 -0.2769 0.01990 0.01170 -0.0826 0.9486 0.3973
-4.000 -0.2477 0.01991 0.01156 -0.0832 0.9466 0.4165
-3.750 -0.2176 0.01988 0.01141 -0.0839 0.9449 0.4299
-3.500 -0.1869 0.01988 0.01130 -0.0848 0.9434 0.4421
-3.250 -0.1618 0.01986 0.01115 -0.0846 0.9408 0.4533
-3.000 -0.1370 0.01985 0.01107 -0.0843 0.9380 0.4648
-2.750 -0.1096 0.01986 0.01103 -0.0845 0.9355 0.4769
-2.500 -0.0803 0.01990 0.01101 -0.0851 0.9333 0.4894
-2.250 -0.0497 0.01995 0.01102 -0.0859 0.9314 0.5025
-2.000 -0.0177 0.02002 0.01106 -0.0870 0.9297 0.5159
-1.750 0.0025 0.02008 0.01107 -0.0859 0.9256 0.5282
-1.500 0.0292 0.02016 0.01115 -0.0859 0.9225 0.5413
-1.250 0.0585 0.02024 0.01125 -0.0865 0.9200 0.5552
-1.000 0.0900 0.02034 0.01136 -0.0874 0.9178 0.5694
-0.750 0.1164 0.02045 0.01149 -0.0874 0.9147 0.5834
-0.500 0.1398 0.02057 0.01165 -0.0868 0.9104 0.5973
-0.250 0.1688 0.02068 0.01181 -0.0873 0.9073 0.6120
0.000 0.2006 0.02078 0.01197 -0.0883 0.9048 0.6278
0.250 0.2260 0.02092 0.01218 -0.0880 0.9008 0.6428
0.500 0.2507 0.02105 0.01239 -0.0877 0.8960 0.6584
0.750 0.2816 0.02115 0.01258 -0.0884 0.8928 0.6744
1.250 0.3340 0.02139 0.01303 -0.0880 0.8833 0.7069
1.500 0.3656 0.02144 0.01324 -0.0887 0.8795 0.7247
1.750 0.3952 0.02150 0.01344 -0.0890 0.8753 0.7425
2.000 0.4176 0.02160 0.01368 -0.0880 0.8685 0.7606
2.250 0.4516 0.02155 0.01379 -0.0890 0.8649 0.7809
2.500 0.4712 0.02162 0.01404 -0.0874 0.8567 0.8013
2.750 0.5043 0.02143 0.01410 -0.0880 0.8521 0.8244
3.000 0.5242 0.02138 0.01424 -0.0862 0.8430 0.8510
3.250 0.5584 0.02097 0.01406 -0.0866 0.8380 0.8832
3.500 0.5827 0.02066 0.01399 -0.0855 0.8272 0.9461
3.750 0.6165 0.02022 0.01373 -0.0862 0.8155 1.0000
4.000 0.6551 0.01938 0.01315 -0.0870 0.8009 1.0000
4.250 0.6840 0.01845 0.01237 -0.0858 0.7764 1.0000
4.500 0.7047 0.01788 0.01195 -0.0835 0.7425 1.0000
4.750 0.7318 0.01712 0.01128 -0.0819 0.6859 1.0000
5.000 0.8000 0.01693 0.00929 -0.0858 0.3537 1.0000
5.250 0.8073 0.01900 0.01022 -0.0830 0.1714 1.0000
5.500 0.8222 0.02068 0.01129 -0.0814 0.0858 1.0000
5.750 0.8380 0.02219 0.01251 -0.0796 0.0501 1.0000
6.000 0.8555 0.02349 0.01381 -0.0779 0.0324 1.0000
6.250 0.8709 0.02508 0.01554 -0.0760 0.0252 1.0000
6.500 0.8901 0.02649 0.01712 -0.0744 0.0210 1.0000
6.750 0.9101 0.02785 0.01851 -0.0735 0.0166 1.0000
7.000 0.9355 0.03020 0.02099 -0.0732 0.0147 1.0000
7.250 0.9664 0.03259 0.02363 -0.0736 0.0139 1.0000
7.500 0.9968 0.03539 0.02675 -0.0737 0.0132 1.0000
7.750 1.0226 0.03847 0.03023 -0.0732 0.0129 1.0000
8.000 1.0423 0.04175 0.03396 -0.0718 0.0126 1.0000
8.250 1.0558 0.04519 0.03786 -0.0696 0.0125 1.0000
8.500 1.0640 0.04876 0.04188 -0.0669 0.0125 1.0000
8.750 1.0669 0.05240 0.04594 -0.0637 0.0125 1.0000
9.000 1.0651 0.05605 0.04998 -0.0603 0.0125 1.0000
9.250 1.0578 0.05953 0.05379 -0.0565 0.0125 1.0000
9.500 1.0466 0.06299 0.05754 -0.0526 0.0126 1.0000
9.750 1.0325 0.06662 0.06143 -0.0492 0.0127 1.0000
10.000 1.0163 0.07049 0.06555 -0.0464 0.0127 1.0000
10.250 0.9986 0.07468 0.06995 -0.0445 0.0128 1.0000
10.500 0.9795 0.07932 0.07479 -0.0437 0.0129 1.0000
10.750 0.9597 0.08451 0.08016 -0.0441 0.0130 1.0000
11.000 0.9394 0.09046 0.08626 -0.0459 0.0131 1.0000
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Polar data table (+)
Polar graphs
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