(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: (Dicke 12.28%) (e171-il) Reynolds number: 50,000 Max Cl/Cd: 29.17 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e171-il-50000.txt Download as CSV file: xf-e171-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: (Dicke 12.28%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6299 0.11360 0.10665 -0.0033 1.0000 0.1464
-11.000 -0.6794 0.09901 0.09233 -0.0157 1.0000 0.1258
-10.750 -0.7445 0.08553 0.07884 -0.0275 1.0000 0.1104
-10.500 -0.7530 0.08010 0.07340 -0.0288 1.0000 0.1092
-10.250 -0.7713 0.07505 0.06831 -0.0300 1.0000 0.1078
-10.000 -0.7931 0.07053 0.06371 -0.0296 1.0000 0.1062
-9.750 -0.8149 0.06613 0.05913 -0.0285 1.0000 0.1039
-9.500 -0.8319 0.06179 0.05449 -0.0270 1.0000 0.1029
-9.250 -0.8407 0.05766 0.05003 -0.0253 1.0000 0.1025
-9.000 -0.8426 0.05378 0.04579 -0.0235 1.0000 0.1035
-8.750 -0.8400 0.04996 0.04156 -0.0216 1.0000 0.1044
-8.500 -0.8327 0.04622 0.03736 -0.0196 1.0000 0.1056
-8.250 -0.8225 0.04290 0.03349 -0.0176 1.0000 0.1088
-8.000 -0.8054 0.03991 0.03037 -0.0164 1.0000 0.1166
-7.750 -0.7881 0.03715 0.02708 -0.0146 1.0000 0.1241
-7.500 -0.7642 0.03439 0.02423 -0.0137 1.0000 0.1371
-7.250 -0.7404 0.03186 0.02190 -0.0127 1.0000 0.1579
-7.000 -0.7200 0.02950 0.01973 -0.0111 1.0000 0.1902
-6.750 -0.7068 0.02718 0.01789 -0.0086 1.0000 0.2410
-6.500 -0.7016 0.02499 0.01647 -0.0049 1.0000 0.3177
-6.250 -0.6987 0.02394 0.01635 0.0005 1.0000 0.4197
-6.000 -0.6884 0.02481 0.01760 0.0064 1.0000 0.5060
-5.750 -0.6708 0.02630 0.01909 0.0118 1.0000 0.5649
-5.500 -0.6468 0.02796 0.02068 0.0167 1.0000 0.6090
-5.250 -0.6152 0.02971 0.02226 0.0210 1.0000 0.6449
-5.000 -0.5885 0.03062 0.02298 0.0247 1.0000 0.6767
-4.750 -0.5568 0.03141 0.02352 0.0274 1.0000 0.7055
-4.500 -0.5199 0.03198 0.02384 0.0289 1.0000 0.7320
-4.250 -0.4887 0.03202 0.02367 0.0301 1.0000 0.7567
-4.000 -0.4575 0.03188 0.02333 0.0306 1.0000 0.7799
-3.750 -0.4078 0.03185 0.02300 0.0282 1.0000 0.8015
-3.500 -0.3687 0.03145 0.02241 0.0264 1.0000 0.8218
-3.250 -0.3478 0.03084 0.02168 0.0270 1.0000 0.8403
-3.000 -0.2951 0.03035 0.02098 0.0224 1.0000 0.8573
-2.750 -0.2582 0.02976 0.02028 0.0199 1.0000 0.8733
-2.500 -0.2282 0.02920 0.01964 0.0182 1.0000 0.8885
-2.250 -0.2020 0.02869 0.01906 0.0169 1.0000 0.9032
-2.000 -0.1783 0.02827 0.01860 0.0158 1.0000 0.9173
-1.750 -0.1538 0.02791 0.01819 0.0142 1.0000 0.9312
-1.500 -0.1278 0.02760 0.01782 0.0121 1.0000 0.9449
-1.250 -0.0988 0.02732 0.01750 0.0093 1.0000 0.9583
-1.000 -0.0657 0.02705 0.01720 0.0055 1.0000 0.9717
-0.750 -0.0277 0.02678 0.01691 0.0007 1.0000 0.9849
-0.500 0.0160 0.02649 0.01660 -0.0054 1.0000 0.9983
-0.250 0.0116 0.02659 0.01671 -0.0033 1.0000 1.0000
0.000 0.0000 0.02664 0.01677 0.0000 1.0000 1.0000
0.250 -0.0117 0.02659 0.01671 0.0033 1.0000 1.0000
0.500 -0.0160 0.02648 0.01660 0.0054 0.9983 1.0000
0.750 0.0275 0.02677 0.01690 -0.0006 0.9849 1.0000
1.000 0.0655 0.02704 0.01720 -0.0055 0.9717 1.0000
1.250 0.0983 0.02730 0.01749 -0.0092 0.9584 1.0000
1.500 0.1271 0.02758 0.01781 -0.0120 0.9450 1.0000
1.750 0.1535 0.02790 0.01818 -0.0141 0.9313 1.0000
2.000 0.1776 0.02826 0.01858 -0.0157 0.9174 1.0000
2.250 0.2021 0.02868 0.01906 -0.0170 0.9032 1.0000
2.500 0.2275 0.02919 0.01961 -0.0181 0.8887 1.0000
2.750 0.2581 0.02975 0.02027 -0.0199 0.8733 1.0000
3.000 0.2950 0.03034 0.02097 -0.0224 0.8573 1.0000
3.250 0.3473 0.03084 0.02170 -0.0269 0.8404 1.0000
3.500 0.3689 0.03144 0.02240 -0.0265 0.8218 1.0000
3.750 0.4075 0.03185 0.02300 -0.0282 0.8016 1.0000
4.000 0.4580 0.03186 0.02331 -0.0307 0.7800 1.0000
4.250 0.4883 0.03202 0.02367 -0.0300 0.7568 1.0000
4.500 0.5200 0.03196 0.02383 -0.0289 0.7320 1.0000
4.750 0.5568 0.03140 0.02351 -0.0274 0.7055 1.0000
5.000 0.5887 0.03061 0.02298 -0.0247 0.6768 1.0000
5.250 0.6152 0.02970 0.02226 -0.0210 0.6449 1.0000
5.500 0.6468 0.02796 0.02067 -0.0167 0.6090 1.0000
5.750 0.6708 0.02630 0.01908 -0.0118 0.5649 1.0000
6.000 0.6884 0.02480 0.01759 -0.0064 0.5061 1.0000
6.250 0.6987 0.02395 0.01635 -0.0005 0.4196 1.0000
6.500 0.7016 0.02499 0.01646 0.0049 0.3178 1.0000
6.750 0.7068 0.02718 0.01789 0.0086 0.2408 1.0000
7.000 0.7200 0.02949 0.01973 0.0111 0.1901 1.0000
7.250 0.7404 0.03185 0.02189 0.0127 0.1579 1.0000
7.500 0.7643 0.03439 0.02423 0.0137 0.1371 1.0000
7.750 0.7881 0.03717 0.02710 0.0146 0.1241 1.0000
8.000 0.8055 0.03990 0.03035 0.0164 0.1164 1.0000
8.250 0.8227 0.04289 0.03348 0.0176 0.1088 1.0000
8.500 0.8328 0.04622 0.03736 0.0196 0.1056 1.0000
8.750 0.8401 0.04996 0.04156 0.0216 0.1043 1.0000
9.000 0.8427 0.05381 0.04582 0.0235 0.1036 1.0000
9.250 0.8406 0.05768 0.05005 0.0253 0.1027 1.0000
9.500 0.8327 0.06173 0.05442 0.0270 0.1025 1.0000
9.750 0.8149 0.06619 0.05918 0.0285 0.1043 1.0000
10.000 0.7937 0.07061 0.06378 0.0295 0.1064 1.0000
10.250 0.7732 0.07502 0.06828 0.0299 0.1080 1.0000
10.500 0.7545 0.08017 0.07347 0.0288 0.1093 1.0000
10.750 0.7462 0.08555 0.07886 0.0275 0.1105 1.0000
11.000 0.5546 0.09933 0.09295 0.0141 0.1400 1.0000
11.250 0.5608 0.10386 0.09746 0.0141 0.1382 1.0000
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Polar data table (+)
Polar graphs
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