EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Xfoil prediction polar at RE=100,000 Ncrit=5
Details | Polar file |
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Airfoil: EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Reynolds number: 100,000 Max Cl/Cd: 40.09 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e874-il-100000-n5.txt Download as CSV file: xf-e874-il-100000-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 = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.5900 0.09038 0.08557 -0.0086 1.0000 0.0185 -9.000 -0.5958 0.08469 0.07997 -0.0117 1.0000 0.0180 -8.750 -0.6043 0.07830 0.07366 -0.0157 1.0000 0.0175 -8.250 -0.6340 0.06177 0.05707 -0.0271 1.0000 0.0163 -8.000 -0.6434 0.05631 0.05136 -0.0285 1.0000 0.0159 -7.750 -0.6472 0.05176 0.04650 -0.0284 1.0000 0.0156 -7.500 -0.6450 0.04799 0.04237 -0.0276 1.0000 0.0154 -7.250 -0.6400 0.04437 0.03838 -0.0263 1.0000 0.0153 -7.000 -0.6326 0.04089 0.03448 -0.0248 1.0000 0.0152 -6.750 -0.6225 0.03761 0.03077 -0.0231 1.0000 0.0151 -6.500 -0.6102 0.03447 0.02719 -0.0213 1.0000 0.0151 -6.250 -0.5957 0.03154 0.02382 -0.0195 1.0000 0.0152 -6.000 -0.5796 0.02859 0.02037 -0.0177 1.0000 0.0153 -5.750 -0.5614 0.02614 0.01759 -0.0161 1.0000 0.0155 -5.500 -0.5424 0.02396 0.01517 -0.0144 1.0000 0.0160 -5.250 -0.5231 0.02221 0.01323 -0.0128 1.0000 0.0166 -5.000 -0.5036 0.02078 0.01164 -0.0112 1.0000 0.0176 -4.750 -0.4834 0.01958 0.01026 -0.0096 1.0000 0.0192 -4.500 -0.4624 0.01859 0.00907 -0.0082 1.0000 0.0225 -4.250 -0.4417 0.01748 0.00784 -0.0067 1.0000 0.0298 -4.000 -0.4233 0.01574 0.00653 -0.0050 1.0000 0.0856 -3.750 -0.4030 0.01485 0.00613 -0.0040 1.0000 0.2085 -3.500 -0.3812 0.01439 0.00580 -0.0030 1.0000 0.2622 -3.250 -0.3587 0.01396 0.00537 -0.0019 1.0000 0.2921 -3.000 -0.3362 0.01354 0.00498 -0.0009 1.0000 0.3262 -2.750 -0.3137 0.01314 0.00465 0.0002 1.0000 0.3675 -2.500 -0.2912 0.01274 0.00438 0.0012 1.0000 0.4182 -2.250 -0.2687 0.01232 0.00412 0.0022 1.0000 0.4841 -2.000 -0.2454 0.01189 0.00396 0.0032 1.0000 0.5677 -1.750 -0.2226 0.01143 0.00388 0.0045 1.0000 0.6710 -1.500 -0.1608 0.01103 0.00396 -0.0015 1.0000 0.8610 -1.250 -0.0745 0.01110 0.00385 -0.0134 1.0000 0.9825 -1.000 -0.0404 0.01115 0.00378 -0.0151 1.0000 1.0000 -0.750 -0.0210 0.01117 0.00374 -0.0138 0.9993 1.0000 -0.500 0.0224 0.01111 0.00359 -0.0174 0.9750 1.0000 -0.250 0.0655 0.01104 0.00347 -0.0208 0.9460 1.0000 0.000 0.1140 0.01100 0.00336 -0.0252 0.9132 1.0000 0.250 0.1658 0.01094 0.00324 -0.0301 0.8746 1.0000 0.500 0.2112 0.01093 0.00312 -0.0336 0.8302 1.0000 0.750 0.2457 0.01103 0.00308 -0.0346 0.7876 1.0000 1.000 0.2741 0.01118 0.00310 -0.0345 0.7509 1.0000 1.250 0.3003 0.01136 0.00322 -0.0340 0.7196 1.0000 1.500 0.3265 0.01154 0.00333 -0.0335 0.6920 1.0000 1.750 0.3523 0.01174 0.00348 -0.0329 0.6679 1.0000 2.000 0.3775 0.01194 0.00366 -0.0323 0.6466 1.0000 2.250 0.4025 0.01216 0.00388 -0.0316 0.6276 1.0000 2.500 0.4274 0.01238 0.00420 -0.0309 0.6099 1.0000 2.750 0.4522 0.01262 0.00449 -0.0302 0.5940 1.0000 3.000 0.4768 0.01287 0.00482 -0.0294 0.5789 1.0000 3.250 0.5014 0.01313 0.00519 -0.0285 0.5638 1.0000 3.500 0.5255 0.01339 0.00559 -0.0276 0.5469 1.0000 3.750 0.5460 0.01362 0.00587 -0.0257 0.5050 1.0000 4.000 0.5586 0.01413 0.00577 -0.0224 0.3618 1.0000 4.250 0.5639 0.01699 0.00681 -0.0194 0.0511 1.0000 4.500 0.5816 0.01836 0.00810 -0.0174 0.0277 1.0000 4.750 0.6018 0.01925 0.00923 -0.0158 0.0223 1.0000 5.000 0.6199 0.02038 0.01053 -0.0139 0.0198 1.0000 5.250 0.6365 0.02175 0.01202 -0.0118 0.0184 1.0000 5.500 0.6524 0.02373 0.01406 -0.0096 0.0174 1.0000 5.750 0.6729 0.02548 0.01591 -0.0080 0.0169 1.0000 6.000 0.6946 0.02741 0.01812 -0.0065 0.0165 1.0000 6.250 0.7162 0.02949 0.02049 -0.0049 0.0159 1.0000 6.500 0.7365 0.03148 0.02283 -0.0033 0.0147 1.0000 6.750 0.7548 0.03365 0.02538 -0.0016 0.0135 1.0000 7.000 0.7709 0.03600 0.02809 0.0001 0.0125 1.0000 7.250 0.7842 0.03902 0.03154 0.0022 0.0124 1.0000 7.500 0.7945 0.04227 0.03523 0.0043 0.0126 1.0000 7.750 0.8017 0.04571 0.03908 0.0065 0.0127 1.0000 8.000 0.8050 0.04942 0.04317 0.0085 0.0129 1.0000 8.250 0.8055 0.05308 0.04716 0.0104 0.0132 1.0000 8.500 0.8018 0.05684 0.05121 0.0120 0.0134 1.0000 8.750 0.7932 0.06076 0.05536 0.0134 0.0135 1.0000 9.000 0.7803 0.06432 0.05909 0.0147 0.0137 1.0000 9.250 0.7644 0.06809 0.06298 0.0148 0.0139 1.0000 9.500 0.7476 0.07297 0.06797 0.0121 0.0139 1.0000 9.750 0.7331 0.07895 0.07402 0.0075 0.0141 1.0000 10.000 0.7190 0.08664 0.08174 0.0017 0.0142 1.0000 |
Polar data table (+)
Polar graphs
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