DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: DU86-084/18 8.44% (du8608418-il) Reynolds number: 50,000 Max Cl/Cd: 32.27 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du8608418-il-50000.txt Download as CSV file: xf-du8608418-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: DU86-084/18 8.44%
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5052 0.09635 0.09009 0.0000 1.0000 0.3023
-8.000 -0.5031 0.09310 0.08690 0.0000 1.0000 0.3173
-7.750 -0.5124 0.09067 0.08458 -0.0003 1.0000 0.3340
-7.500 -0.5063 0.08689 0.08087 0.0003 1.0000 0.3497
-7.250 -0.4002 0.07231 0.06665 -0.0048 1.0000 0.3664
-7.000 -0.3953 0.06846 0.06285 -0.0039 1.0000 0.3833
-6.750 -0.3964 0.06466 0.05912 -0.0031 1.0000 0.3964
-6.250 -0.5671 0.05890 0.05250 -0.0245 1.0000 0.1637
-6.000 -0.5747 0.05297 0.04555 -0.0242 1.0000 0.1271
-5.750 -0.5625 0.04861 0.04119 -0.0225 1.0000 0.1191
-5.500 -0.5535 0.04455 0.03651 -0.0205 1.0000 0.1096
-5.250 -0.5413 0.04081 0.03223 -0.0185 1.0000 0.1040
-5.000 -0.5250 0.03774 0.02821 -0.0162 1.0000 0.0994
-4.750 -0.5059 0.03475 0.02482 -0.0145 1.0000 0.0990
-4.500 -0.4859 0.03197 0.02181 -0.0131 1.0000 0.1032
-4.250 -0.4643 0.02999 0.01944 -0.0116 1.0000 0.1116
-4.000 -0.4402 0.02766 0.01694 -0.0102 1.0000 0.1192
-3.750 -0.4151 0.02571 0.01487 -0.0089 1.0000 0.1359
-3.500 -0.1542 0.01957 0.01137 -0.0370 1.0000 1.0000
-3.250 -0.1550 0.01926 0.01080 -0.0338 1.0000 1.0000
-3.000 -0.1523 0.01907 0.01030 -0.0307 1.0000 1.0000
-2.750 -0.1473 0.01895 0.00992 -0.0277 1.0000 1.0000
-2.500 -0.1405 0.01886 0.00958 -0.0248 1.0000 1.0000
-2.250 -0.1325 0.01880 0.00929 -0.0220 1.0000 1.0000
-2.000 -0.1235 0.01876 0.00903 -0.0193 1.0000 1.0000
-1.750 -0.1137 0.01874 0.00882 -0.0166 1.0000 1.0000
-1.500 -0.1034 0.01874 0.00863 -0.0141 1.0000 1.0000
-1.250 -0.0927 0.01875 0.00844 -0.0116 1.0000 1.0000
-1.000 -0.0816 0.01877 0.00831 -0.0092 1.0000 1.0000
-0.750 -0.0701 0.01881 0.00822 -0.0068 1.0000 1.0000
-0.500 -0.0582 0.01887 0.00815 -0.0045 1.0000 1.0000
-0.250 -0.0460 0.01894 0.00812 -0.0023 1.0000 1.0000
0.000 -0.0335 0.01904 0.00812 -0.0002 1.0000 1.0000
0.250 -0.0207 0.01915 0.00812 0.0019 1.0000 1.0000
0.500 -0.0073 0.01929 0.00819 0.0038 1.0000 1.0000
0.750 0.0068 0.01947 0.00830 0.0055 1.0000 1.0000
1.000 0.0216 0.01967 0.00846 0.0070 1.0000 1.0000
1.250 0.0369 0.01992 0.00868 0.0084 1.0000 1.0000
1.500 0.0527 0.02020 0.00894 0.0096 1.0000 1.0000
1.750 0.0688 0.02053 0.00926 0.0107 1.0000 1.0000
2.000 0.0851 0.02091 0.00965 0.0116 1.0000 1.0000
2.250 0.1014 0.02133 0.01010 0.0124 1.0000 1.0000
2.500 0.1177 0.02182 0.01062 0.0131 1.0000 1.0000
2.750 0.1338 0.02237 0.01123 0.0137 1.0000 1.0000
3.000 0.1496 0.02300 0.01195 0.0141 1.0000 1.0000
3.250 0.1650 0.02371 0.01274 0.0145 1.0000 1.0000
3.500 0.2264 0.02543 0.01471 0.0058 0.9777 1.0000
3.750 0.3125 0.02730 0.01701 -0.0062 0.9410 1.0000
4.000 0.3944 0.02845 0.01863 -0.0160 0.8998 1.0000
4.250 0.4789 0.02872 0.01957 -0.0242 0.8530 1.0000
4.500 0.5726 0.02735 0.01898 -0.0305 0.7979 1.0000
4.750 0.6078 0.02538 0.01744 -0.0269 0.7406 1.0000
5.000 0.6455 0.02191 0.01439 -0.0209 0.6618 1.0000
5.250 0.6716 0.02081 0.01238 -0.0139 0.5062 1.0000
5.500 0.6816 0.02254 0.01318 -0.0094 0.3928 1.0000
5.750 0.6973 0.02445 0.01444 -0.0067 0.3144 1.0000
6.000 0.7176 0.02637 0.01604 -0.0048 0.2568 1.0000
6.250 0.7399 0.02837 0.01782 -0.0034 0.2164 1.0000
6.500 0.7628 0.03058 0.02007 -0.0021 0.1878 1.0000
6.750 0.7849 0.03291 0.02261 -0.0007 0.1656 1.0000
7.000 0.8048 0.03551 0.02539 0.0007 0.1472 1.0000
7.250 0.8243 0.03865 0.02883 0.0023 0.1343 1.0000
7.500 0.8393 0.04147 0.03196 0.0040 0.1205 1.0000
7.750 0.8505 0.04543 0.03662 0.0061 0.1155 1.0000
8.000 0.8631 0.04894 0.04029 0.0076 0.1072 1.0000
8.250 0.8650 0.05294 0.04494 0.0097 0.1034 1.0000
8.500 0.8650 0.05756 0.05003 0.0114 0.1032 1.0000
8.750 0.8608 0.06250 0.05535 0.0127 0.1046 1.0000
9.000 0.8555 0.06749 0.06060 0.0136 0.1064 1.0000
9.250 0.8561 0.07269 0.06591 0.0141 0.1083 1.0000
9.500 0.8111 0.07794 0.07151 0.0133 0.1147 1.0000
9.750 0.7884 0.08360 0.07720 0.0117 0.1186 1.0000
10.000 0.7550 0.09225 0.08583 0.0050 0.1309 1.0000
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Polar data table (+)
Polar graphs
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