EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Reynolds number: 500,000 Max Cl/Cd: 65.53 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e874-il-500000.txt Download as CSV file: xf-e874-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5734 0.08412 0.08195 -0.0118 1.0000 0.0150
-8.750 -0.5772 0.07821 0.07608 -0.0153 1.0000 0.0150
-7.000 -0.6375 0.03891 0.03555 -0.0243 1.0000 0.0157
-6.750 -0.6367 0.03403 0.03041 -0.0222 1.0000 0.0166
-6.500 -0.6255 0.03135 0.02756 -0.0204 1.0000 0.0174
-6.250 -0.6119 0.02910 0.02509 -0.0187 1.0000 0.0183
-6.000 -0.5978 0.02673 0.02246 -0.0166 1.0000 0.0195
-5.750 -0.5836 0.02175 0.01680 -0.0124 1.0000 0.0124
-5.500 -0.5680 0.01768 0.01214 -0.0089 1.0000 0.0100
-5.250 -0.5479 0.01609 0.01034 -0.0071 1.0000 0.0103
-5.000 -0.5264 0.01532 0.00950 -0.0059 1.0000 0.0116
-4.750 -0.5052 0.01426 0.00832 -0.0044 1.0000 0.0122
-4.500 -0.4849 0.01298 0.00688 -0.0025 1.0000 0.0117
-4.250 -0.4645 0.01199 0.00578 -0.0008 1.0000 0.0114
-4.000 -0.4435 0.01119 0.00486 0.0009 1.0000 0.0113
-3.750 -0.4217 0.01058 0.00410 0.0023 1.0000 0.0115
-3.500 -0.3992 0.01010 0.00351 0.0036 1.0000 0.0125
-3.250 -0.3763 0.00974 0.00304 0.0048 1.0000 0.0144
-3.000 -0.3561 0.00876 0.00252 0.0062 0.9998 0.1196
-2.750 -0.3176 0.00825 0.00240 0.0035 0.9960 0.2076
-2.500 -0.2797 0.00792 0.00225 0.0010 0.9914 0.2612
-2.250 -0.2428 0.00747 0.00211 -0.0013 0.9859 0.3435
-2.000 -0.2091 0.00700 0.00197 -0.0028 0.9784 0.4315
-1.750 -0.1761 0.00659 0.00182 -0.0040 0.9682 0.5089
-1.500 -0.1459 0.00614 0.00167 -0.0045 0.9544 0.5916
-1.250 -0.1129 0.00565 0.00151 -0.0054 0.9395 0.6874
-1.000 -0.0714 0.00510 0.00140 -0.0082 0.9230 0.8124
-0.750 0.0260 0.00498 0.00155 -0.0233 0.9121 0.9311
-0.500 0.0910 0.00514 0.00151 -0.0311 0.8591 0.9537
0.000 0.1583 0.00576 0.00164 -0.0331 0.7541 0.9838
0.250 0.2015 0.00596 0.00165 -0.0364 0.7127 0.9915
0.500 0.2465 0.00610 0.00162 -0.0403 0.6750 0.9984
1.000 0.2987 0.00632 0.00159 -0.0396 0.6180 1.0000
1.250 0.3222 0.00642 0.00163 -0.0387 0.5955 1.0000
1.500 0.3459 0.00654 0.00167 -0.0379 0.5752 1.0000
1.750 0.3700 0.00664 0.00172 -0.0371 0.5565 1.0000
2.000 0.3942 0.00675 0.00179 -0.0363 0.5391 1.0000
2.250 0.4184 0.00688 0.00186 -0.0355 0.5218 1.0000
2.500 0.4425 0.00700 0.00196 -0.0347 0.4984 1.0000
2.750 0.4650 0.00721 0.00199 -0.0336 0.4472 1.0000
3.000 0.4879 0.00745 0.00207 -0.0326 0.3997 1.0000
3.250 0.5105 0.00779 0.00220 -0.0316 0.3357 1.0000
3.500 0.5194 0.01012 0.00313 -0.0286 0.0174 1.0000
3.750 0.5426 0.01053 0.00366 -0.0275 0.0142 1.0000
4.000 0.5643 0.01113 0.00433 -0.0261 0.0105 1.0000
4.250 0.5829 0.01218 0.00554 -0.0241 0.0094 1.0000
4.500 0.6039 0.01287 0.00631 -0.0225 0.0088 1.0000
4.750 0.6228 0.01393 0.00747 -0.0205 0.0086 1.0000
5.000 0.6412 0.01533 0.00899 -0.0184 0.0085 1.0000
5.250 0.6601 0.01726 0.01105 -0.0162 0.0090 1.0000
5.500 0.6817 0.01897 0.01284 -0.0147 0.0102 1.0000
5.750 0.7094 0.02332 0.01779 -0.0112 0.0227 1.0000
6.000 0.7286 0.02503 0.01971 -0.0095 0.0210 1.0000
6.250 0.7465 0.02696 0.02177 -0.0079 0.0197 1.0000
6.500 0.7612 0.02980 0.02475 -0.0062 0.0184 1.0000
6.750 0.7576 0.03730 0.03280 -0.0025 0.0172 1.0000
7.000 0.7689 0.03942 0.03522 -0.0001 0.0171 1.0000
7.250 0.7912 0.03865 0.03470 0.0020 0.0157 1.0000
7.500 0.8032 0.04098 0.03728 0.0043 0.0146 1.0000
7.750 0.8105 0.04392 0.04047 0.0067 0.0137 1.0000
8.000 0.8142 0.04714 0.04393 0.0089 0.0132 1.0000
8.250 0.8152 0.05036 0.04736 0.0110 0.0128 1.0000
8.500 0.8128 0.05369 0.05086 0.0130 0.0125 1.0000
8.750 0.8057 0.05716 0.05450 0.0148 0.0122 1.0000
9.000 0.7935 0.06051 0.05799 0.0168 0.0121 1.0000
9.250 0.7747 0.06379 0.06138 0.0184 0.0122 1.0000
9.500 0.7539 0.06862 0.06632 0.0160 0.0123 1.0000
9.750 0.7336 0.07601 0.07379 0.0093 0.0127 1.0000
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Polar data table (+)
Polar graphs
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