GOE 396 AIRFOIL (goe396-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 396 AIRFOIL (goe396-il) Reynolds number: 500,000 Max Cl/Cd: 121.3 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe396-il-500000.txt Download as CSV file: xf-goe396-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 396 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2378 0.09443 0.09239 -0.0325 1.0000 0.0101
-8.500 -0.2378 0.09179 0.08979 -0.0321 1.0000 0.0101
-8.250 -0.2401 0.08955 0.08760 -0.0310 1.0000 0.0101
-8.000 -0.2378 0.08662 0.08469 -0.0315 0.9989 0.0101
-7.750 -0.2286 0.07986 0.07796 -0.0340 0.9966 0.0105
-7.500 -0.2139 0.07539 0.07349 -0.0364 0.9935 0.0109
-7.250 -0.1998 0.07135 0.06944 -0.0396 0.9885 0.0111
-7.000 -0.1839 0.06719 0.06526 -0.0435 0.9838 0.0114
-6.750 -0.1694 0.06322 0.06129 -0.0473 0.9760 0.0118
-6.500 -0.1502 0.05878 0.05684 -0.0526 0.9703 0.0123
-6.250 -0.1308 0.05442 0.05247 -0.0579 0.9616 0.0131
-6.000 -0.1079 0.04992 0.04794 -0.0639 0.9538 0.0138
-5.750 -0.0846 0.04562 0.04359 -0.0699 0.9429 0.0151
-5.500 -0.1173 0.06094 0.05880 -0.0722 0.9597 0.0141
-5.250 -0.0689 0.05671 0.05448 -0.0831 0.9522 0.0162
-3.000 0.1998 0.01786 0.01365 -0.1119 0.8621 0.0173
-2.500 0.2493 0.01199 0.00659 -0.1105 0.8468 0.0179
-2.250 0.2749 0.01130 0.00576 -0.1100 0.8380 0.0204
-2.000 0.3012 0.01086 0.00515 -0.1095 0.8291 0.0237
-1.750 0.3277 0.01034 0.00441 -0.1088 0.8200 0.0262
-1.500 0.3527 0.00922 0.00309 -0.1080 0.8108 0.0313
-1.250 0.3792 0.00905 0.00284 -0.1076 0.8029 0.0379
-1.000 0.4048 0.00855 0.00225 -0.1070 0.7947 0.0439
-0.750 0.4309 0.00838 0.00204 -0.1065 0.7856 0.0508
-0.500 0.4569 0.00817 0.00176 -0.1060 0.7767 0.0562
-0.250 0.4826 0.00797 0.00158 -0.1054 0.7663 0.0746
0.000 0.5084 0.00785 0.00156 -0.1049 0.7547 0.1294
0.250 0.5346 0.00782 0.00151 -0.1044 0.7434 0.1466
0.500 0.5607 0.00778 0.00147 -0.1040 0.7328 0.1619
0.750 0.5866 0.00774 0.00144 -0.1036 0.7216 0.1804
1.000 0.6124 0.00769 0.00143 -0.1031 0.7096 0.2084
1.250 0.6378 0.00760 0.00146 -0.1026 0.6972 0.2653
1.500 0.6569 0.00677 0.00155 -0.1011 0.6846 0.6796
1.750 0.7179 0.00628 0.00154 -0.1087 0.6687 1.0000
2.000 0.7429 0.00640 0.00158 -0.1080 0.6532 1.0000
2.250 0.7681 0.00653 0.00163 -0.1074 0.6390 1.0000
2.500 0.7931 0.00666 0.00170 -0.1068 0.6246 1.0000
2.750 0.8181 0.00680 0.00179 -0.1062 0.6103 1.0000
3.000 0.8430 0.00695 0.00189 -0.1055 0.5949 1.0000
3.250 0.8657 0.00720 0.00202 -0.1044 0.5620 1.0000
3.500 0.8889 0.00745 0.00215 -0.1035 0.5302 1.0000
3.750 0.9104 0.00781 0.00231 -0.1023 0.4833 1.0000
4.000 0.9302 0.00836 0.00255 -0.1008 0.4201 1.0000
4.250 0.9478 0.00916 0.00291 -0.0991 0.3322 1.0000
4.500 0.9554 0.01105 0.00380 -0.0960 0.1389 1.0000
4.750 0.9748 0.01181 0.00433 -0.0946 0.0892 1.0000
5.000 0.9919 0.01284 0.00501 -0.0927 0.0196 1.0000
5.250 1.0144 0.01328 0.00558 -0.0916 0.0174 1.0000
5.500 1.0359 0.01384 0.00626 -0.0903 0.0159 1.0000
5.750 1.0558 0.01455 0.00708 -0.0888 0.0144 1.0000
6.000 1.0729 0.01551 0.00814 -0.0868 0.0127 1.0000
6.250 1.0864 0.01682 0.00957 -0.0842 0.0119 1.0000
6.500 1.0945 0.01885 0.01176 -0.0807 0.0113 1.0000
6.750 1.1095 0.02063 0.01361 -0.0784 0.0112 1.0000
7.000 1.1300 0.02173 0.01475 -0.0770 0.0116 1.0000
7.250 1.1520 0.02229 0.01538 -0.0758 0.0123 1.0000
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Polar data table (+)
Polar graphs
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