GOE 451 AIRFOIL (modified line 6) (goe451-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 451 AIRFOIL (modified line 6) (goe451-il) Reynolds number: 500,000 Max Cl/Cd: 37.28 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe451-il-500000.txt Download as CSV file: xf-goe451-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 451 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
------ -------- --------- --------- -------- -------- --------
-6.250 -0.2688 0.07114 0.06613 -0.0633 0.0365 0.0080
-6.000 -0.2600 0.06600 0.06101 -0.0653 0.0345 0.0088
-5.750 -0.2428 0.06282 0.05784 -0.0681 0.0311 0.0092
-5.500 -0.2113 0.04484 0.04018 -0.0623 0.0306 0.0110
-2.500 0.1332 0.01979 0.01261 -0.1035 0.0108 0.0151
-2.000 0.1898 0.01550 0.00735 -0.1035 0.0106 0.0116
-1.750 0.2176 0.01384 0.00533 -0.1032 0.0106 0.0111
-1.500 0.2442 0.01270 0.00402 -0.1029 0.0106 0.0123
-1.250 0.2699 0.01261 0.00381 -0.1027 0.0106 0.0170
-1.000 0.2953 0.01271 0.00389 -0.1030 0.0104 0.0216
-0.750 0.3216 0.01259 0.00376 -0.1033 0.0088 0.0246
1.500 0.5339 0.01763 0.00826 -0.1030 0.0073 0.0627
1.750 0.5585 0.01815 0.00895 -0.1034 0.0072 0.1661
2.000 0.5827 0.01804 0.00894 -0.1034 0.0072 0.1833
2.250 0.5997 0.01651 0.00916 -0.1018 0.0071 1.0000
2.500 0.6241 0.01708 0.00970 -0.1018 0.0071 1.0000
2.750 0.6488 0.01785 0.01053 -0.1018 0.0070 1.0000
3.000 0.6733 0.01806 0.01075 -0.1017 0.0062 1.0000
3.250 0.7044 0.02138 0.01225 -0.1032 0.0047 0.0779
3.500 0.7272 0.02643 0.01723 -0.1035 0.0044 0.0725
3.750 0.7512 0.02710 0.01807 -0.1030 0.0044 0.0709
4.000 0.7748 0.02817 0.01931 -0.1026 0.0044 0.0717
4.250 0.7981 0.02938 0.02072 -0.1021 0.0043 0.0745
4.500 0.8212 0.03059 0.02218 -0.1016 0.0043 0.0800
4.750 0.8441 0.03179 0.02363 -0.1010 0.0043 0.0870
7.750 1.0642 0.05367 0.04946 -0.0912 0.0017 1.0000
8.000 1.0746 0.05765 0.05367 -0.0899 0.0019 1.0000
8.250 1.0842 0.06186 0.05808 -0.0888 0.0019 1.0000
8.500 1.0928 0.06613 0.06253 -0.0876 0.0019 1.0000
8.750 1.1005 0.07040 0.06698 -0.0865 0.0020 1.0000
9.000 1.1070 0.07466 0.07141 -0.0854 0.0020 1.0000
9.250 1.1121 0.07889 0.07581 -0.0843 0.0020 1.0000
9.500 1.1155 0.08318 0.08026 -0.0832 0.0020 1.0000
9.750 1.1172 0.08735 0.08459 -0.0822 0.0020 1.0000
10.000 1.1167 0.09153 0.08892 -0.0811 0.0020 1.0000
10.250 1.1139 0.09550 0.09303 -0.0800 0.0020 1.0000
10.500 1.1084 0.09945 0.09710 -0.0789 0.0020 1.0000
10.750 1.0999 0.10326 0.10103 -0.0779 0.0020 1.0000
11.000 1.0852 0.10641 0.10427 -0.0759 0.0020 1.0000
11.250 1.0694 0.10993 0.10787 -0.0752 0.0020 1.0000
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Polar data table (+)
Polar graphs
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