E184 (8.33%) (e184-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E184 (8.33%) (e184-il) Reynolds number: 500,000 Max Cl/Cd: 63.93 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e184-il-500000-n5.txt Download as CSV file: xf-e184-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E184 (8.33%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.7104 0.08277 0.08091 0.0220 1.0000 0.0078
-9.000 -0.7260 0.07557 0.07377 0.0164 1.0000 0.0077
-8.750 -0.7487 0.06747 0.06568 0.0098 1.0000 0.0076
-8.500 -0.7668 0.05668 0.05471 0.0046 0.9768 0.0075
-8.250 -0.7884 0.04527 0.04279 0.0042 0.8967 0.0076
-8.000 -0.7913 0.03941 0.03641 0.0055 0.8702 0.0078
-7.750 -0.7828 0.03570 0.03225 0.0067 0.8508 0.0079
-7.500 -0.7799 0.02986 0.02571 0.0085 0.8352 0.0082
-7.250 -0.7673 0.02610 0.02145 0.0099 0.8216 0.0085
-7.000 -0.7483 0.02395 0.01893 0.0109 0.8090 0.0088
-6.750 -0.7269 0.02236 0.01707 0.0116 0.7974 0.0091
-6.500 -0.7038 0.02128 0.01578 0.0122 0.7867 0.0095
-6.250 -0.6800 0.02026 0.01455 0.0127 0.7769 0.0100
-6.000 -0.6561 0.01890 0.01295 0.0134 0.7673 0.0102
-5.750 -0.6318 0.01756 0.01136 0.0140 0.7588 0.0105
-5.250 -0.5817 0.01548 0.00889 0.0152 0.7426 0.0112
-5.000 -0.5563 0.01466 0.00789 0.0157 0.7353 0.0116
-4.750 -0.5306 0.01395 0.00705 0.0162 0.7278 0.0121
-4.500 -0.5047 0.01334 0.00631 0.0166 0.7211 0.0125
-4.250 -0.4787 0.01278 0.00565 0.0170 0.7141 0.0128
-4.000 -0.4525 0.01229 0.00506 0.0174 0.7079 0.0130
-3.750 -0.4259 0.01192 0.00461 0.0176 0.7012 0.0134
-3.250 -0.3728 0.01108 0.00358 0.0183 0.6892 0.0141
-3.000 -0.3460 0.01073 0.00312 0.0186 0.6833 0.0145
-2.750 -0.3188 0.01044 0.00274 0.0188 0.6778 0.0151
-2.500 -0.2915 0.01021 0.00243 0.0190 0.6720 0.0164
-2.250 -0.2642 0.01000 0.00218 0.0192 0.6667 0.0193
-2.000 -0.2375 0.00963 0.00193 0.0194 0.6610 0.0507
-1.750 -0.2108 0.00931 0.00175 0.0196 0.6558 0.0957
-1.500 -0.1841 0.00900 0.00161 0.0198 0.6505 0.1441
-1.250 -0.1581 0.00858 0.00148 0.0199 0.6450 0.2250
-0.750 -0.1111 0.00719 0.00124 0.0211 0.6348 0.5436
-0.500 -0.0889 0.00664 0.00117 0.0223 0.6294 0.6770
-0.250 -0.0670 0.00615 0.00113 0.0238 0.6246 0.7975
0.000 -0.0268 0.00591 0.00122 0.0217 0.6188 0.9119
0.250 0.0284 0.00601 0.00129 0.0159 0.6129 0.9484
0.500 0.0642 0.00609 0.00134 0.0143 0.6069 0.9652
0.750 0.0979 0.00617 0.00136 0.0132 0.5999 0.9768
1.000 0.1326 0.00622 0.00138 0.0117 0.5911 0.9845
1.250 0.1712 0.00627 0.00138 0.0094 0.5820 0.9906
1.750 0.2484 0.00634 0.00138 0.0047 0.5593 0.9996
2.000 0.2765 0.00637 0.00138 0.0046 0.5488 1.0000
2.250 0.3029 0.00641 0.00141 0.0049 0.5357 1.0000
2.500 0.3294 0.00647 0.00144 0.0052 0.5222 1.0000
2.750 0.3559 0.00654 0.00148 0.0054 0.5072 1.0000
3.000 0.3825 0.00663 0.00153 0.0057 0.4888 1.0000
3.250 0.4091 0.00674 0.00160 0.0059 0.4660 1.0000
3.500 0.4357 0.00690 0.00171 0.0060 0.4373 1.0000
3.750 0.4622 0.00723 0.00184 0.0061 0.3807 1.0000
4.000 0.4883 0.00825 0.00222 0.0055 0.2370 1.0000
4.250 0.5143 0.00883 0.00252 0.0053 0.1731 1.0000
4.500 0.5401 0.00940 0.00285 0.0053 0.1169 1.0000
4.750 0.5654 0.01010 0.00328 0.0052 0.0579 1.0000
5.000 0.5905 0.01073 0.00371 0.0053 0.0207 1.0000
5.250 0.6158 0.01123 0.00417 0.0055 0.0092 1.0000
5.500 0.6413 0.01159 0.00459 0.0059 0.0082 1.0000
5.750 0.6665 0.01199 0.00507 0.0063 0.0076 1.0000
6.000 0.6914 0.01246 0.00562 0.0066 0.0070 1.0000
6.250 0.7159 0.01297 0.00622 0.0070 0.0062 1.0000
6.500 0.7397 0.01362 0.00695 0.0074 0.0055 1.0000
6.750 0.7626 0.01445 0.00789 0.0080 0.0051 1.0000
7.000 0.7829 0.01583 0.00942 0.0088 0.0047 1.0000
7.250 0.8052 0.01658 0.01025 0.0094 0.0045 1.0000
7.500 0.8265 0.01749 0.01125 0.0102 0.0043 1.0000
7.750 0.8469 0.01854 0.01242 0.0111 0.0043 1.0000
8.000 0.8667 0.01968 0.01373 0.0120 0.0041 1.0000
8.250 0.8855 0.02102 0.01522 0.0131 0.0040 1.0000
8.500 0.9034 0.02250 0.01688 0.0142 0.0039 1.0000
8.750 0.9201 0.02418 0.01876 0.0154 0.0039 1.0000
9.000 0.9352 0.02606 0.02087 0.0167 0.0039 1.0000
9.250 0.9481 0.02814 0.02321 0.0180 0.0038 1.0000
9.500 0.9580 0.03052 0.02586 0.0195 0.0038 1.0000
9.750 0.9637 0.03317 0.02880 0.0211 0.0038 1.0000
10.000 0.9651 0.03594 0.03186 0.0228 0.0038 1.0000
10.250 0.9597 0.03885 0.03502 0.0248 0.0038 1.0000
10.500 0.9484 0.04148 0.03784 0.0267 0.0039 1.0000
10.750 0.9358 0.04491 0.04147 0.0271 0.0039 1.0000
11.000 0.9241 0.04871 0.04546 0.0263 0.0039 1.0000
11.250 0.9071 0.05374 0.05068 0.0243 0.0039 1.0000
11.500 0.8890 0.05956 0.05668 0.0212 0.0039 1.0000
11.750 0.8719 0.06594 0.06321 0.0171 0.0040 1.0000
12.000 0.8519 0.07390 0.07132 0.0116 0.0040 1.0000
12.250 0.8346 0.08266 0.08020 0.0054 0.0040 1.0000
12.500 0.8072 0.09635 0.09401 -0.0029 0.0041 1.0000
12.750 0.7704 0.11296 0.11063 -0.0100 0.0043 1.0000
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Polar data table (+)
Polar graphs
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