EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Reynolds number: 1,000,000 Max Cl/Cd: 63.7 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e874-il-1000000-n5.txt Download as CSV file: xf-e874-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 874 HYDROFOIL AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6093 0.09750 0.09591 -0.0006 1.0000 0.0020
-10.000 -0.6162 0.09168 0.09011 -0.0032 1.0000 0.0019
-9.750 -0.6274 0.08486 0.08333 -0.0064 1.0000 0.0020
-9.500 -0.6344 0.07936 0.07785 -0.0093 1.0000 0.0019
-9.250 -0.6527 0.07128 0.06981 -0.0142 1.0000 0.0019
-8.750 -0.7021 0.04910 0.04749 -0.0285 1.0000 0.0018
-8.500 -0.7159 0.04317 0.04132 -0.0284 1.0000 0.0018
-8.250 -0.7327 0.03639 0.03417 -0.0262 1.0000 0.0017
-8.000 -0.7408 0.03076 0.02811 -0.0230 1.0000 0.0017
-7.750 -0.7425 0.02591 0.02276 -0.0194 1.0000 0.0017
-7.500 -0.7349 0.02265 0.01909 -0.0165 1.0000 0.0018
-7.250 -0.7225 0.02022 0.01632 -0.0140 1.0000 0.0018
-7.000 -0.7061 0.01855 0.01439 -0.0120 1.0000 0.0019
-6.750 -0.6865 0.01758 0.01326 -0.0105 1.0000 0.0020
-6.500 -0.6665 0.01666 0.01217 -0.0091 1.0000 0.0021
-6.250 -0.6423 0.01375 0.00885 -0.0088 0.9981 0.0025
-6.000 -0.6101 0.01292 0.00791 -0.0101 0.9961 0.0028
-5.750 -0.5776 0.01229 0.00720 -0.0114 0.9944 0.0030
-5.500 -0.5493 0.01153 0.00630 -0.0116 0.9917 0.0031
-5.250 -0.5197 0.01095 0.00565 -0.0121 0.9884 0.0034
-5.000 -0.4887 0.01051 0.00515 -0.0129 0.9849 0.0037
-4.750 -0.4639 0.00995 0.00451 -0.0122 0.9791 0.0039
-4.500 -0.4414 0.00946 0.00393 -0.0110 0.9682 0.0039
-4.250 -0.4115 0.00899 0.00337 -0.0114 0.9560 0.0039
-4.000 -0.3636 0.00850 0.00276 -0.0158 0.9415 0.0039
-3.750 -0.3042 0.00813 0.00222 -0.0229 0.9078 0.0040
-3.500 -0.2747 0.00809 0.00192 -0.0232 0.8497 0.0043
-3.250 -0.2510 0.00810 0.00174 -0.0221 0.8018 0.0054
-3.000 -0.2276 0.00799 0.00153 -0.0211 0.7627 0.0190
-2.750 -0.2067 0.00746 0.00123 -0.0198 0.7268 0.1130
-2.500 -0.1822 0.00736 0.00112 -0.0192 0.6966 0.1393
-2.250 -0.1570 0.00730 0.00103 -0.0186 0.6704 0.1586
-2.000 -0.1319 0.00718 0.00095 -0.0181 0.6469 0.1920
-1.750 -0.1074 0.00698 0.00086 -0.0175 0.6259 0.2461
-1.500 -0.0816 0.00691 0.00080 -0.0171 0.6059 0.2701
-1.250 -0.0557 0.00686 0.00075 -0.0167 0.5870 0.2929
-1.000 -0.0298 0.00682 0.00071 -0.0163 0.5679 0.3179
-0.750 -0.0039 0.00676 0.00068 -0.0160 0.5511 0.3456
-0.500 0.0221 0.00670 0.00065 -0.0156 0.5365 0.3757
-0.250 0.0481 0.00663 0.00063 -0.0152 0.5231 0.4080
0.000 0.0741 0.00655 0.00062 -0.0149 0.5106 0.4433
0.250 0.0996 0.00645 0.00063 -0.0144 0.4985 0.4892
0.500 0.1250 0.00633 0.00064 -0.0139 0.4868 0.5392
0.750 0.1500 0.00621 0.00066 -0.0134 0.4764 0.5937
1.000 0.1742 0.00605 0.00069 -0.0126 0.4669 0.6590
1.250 0.1972 0.00583 0.00072 -0.0115 0.4581 0.7363
1.500 0.2179 0.00554 0.00076 -0.0098 0.4495 0.8362
1.750 0.3016 0.00549 0.00100 -0.0225 0.4322 0.9482
2.000 0.3375 0.00565 0.00113 -0.0242 0.4165 0.9655
2.250 0.3617 0.00587 0.00122 -0.0234 0.3844 0.9774
2.500 0.3876 0.00625 0.00135 -0.0231 0.3184 0.9848
2.750 0.4158 0.00742 0.00173 -0.0240 0.1187 0.9894
3.000 0.4466 0.00806 0.00203 -0.0250 0.0323 0.9931
3.250 0.4809 0.00840 0.00228 -0.0265 0.0078 0.9956
3.500 0.5173 0.00863 0.00250 -0.0285 0.0044 0.9977
3.750 0.5544 0.00884 0.00276 -0.0306 0.0039 0.9998
4.000 0.5794 0.00911 0.00306 -0.0301 0.0033 1.0000
4.250 0.6026 0.00946 0.00347 -0.0291 0.0028 1.0000
4.500 0.6249 0.00995 0.00405 -0.0278 0.0025 1.0000
4.750 0.6476 0.01035 0.00452 -0.0267 0.0023 1.0000
5.000 0.6691 0.01091 0.00517 -0.0254 0.0022 1.0000
5.250 0.6899 0.01156 0.00591 -0.0239 0.0021 1.0000
5.500 0.7097 0.01235 0.00684 -0.0222 0.0021 1.0000
5.750 0.7291 0.01322 0.00782 -0.0205 0.0020 1.0000
6.000 0.7477 0.01432 0.00905 -0.0186 0.0020 1.0000
6.250 0.7660 0.01563 0.01051 -0.0166 0.0020 1.0000
6.500 0.7843 0.01711 0.01217 -0.0147 0.0020 1.0000
6.750 0.8020 0.01886 0.01414 -0.0127 0.0021 1.0000
7.000 0.8177 0.02116 0.01672 -0.0103 0.0021 1.0000
7.250 0.8309 0.02390 0.01978 -0.0076 0.0022 1.0000
7.500 0.8413 0.02701 0.02322 -0.0047 0.0022 1.0000
7.750 0.8479 0.03058 0.02713 -0.0015 0.0023 1.0000
8.000 0.8479 0.03495 0.03187 0.0021 0.0024 1.0000
9.250 0.8190 0.05650 0.05455 0.0169 0.0037 1.0000
9.500 0.7983 0.05976 0.05792 0.0191 0.0037 1.0000
9.750 0.7796 0.06409 0.06236 0.0171 0.0037 1.0000
10.000 0.7552 0.07184 0.07021 0.0103 0.0038 1.0000
10.250 0.7385 0.08097 0.07941 0.0022 0.0041 1.0000
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Polar data table (+)
Polar graphs
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