GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 6K AIRFOIL (goe06k-il) Reynolds number: 50,000 Max Cl/Cd: 26.39 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe06k-il-50000.txt Download as CSV file: xf-goe06k-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 6K AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4986 0.10723 0.10072 -0.0244 1.0000 0.1835
-7.750 -0.4846 0.10261 0.09610 -0.0222 1.0000 0.1951
-7.500 -0.5128 0.10218 0.09584 -0.0211 1.0000 0.1974
-7.250 -0.5046 0.09826 0.09195 -0.0183 1.0000 0.2096
-7.000 -0.5070 0.09531 0.08907 -0.0162 1.0000 0.2221
-6.750 -0.5108 0.09255 0.08639 -0.0142 1.0000 0.2341
-6.500 -0.5160 0.08994 0.08386 -0.0122 1.0000 0.2488
-6.250 -0.5215 0.08733 0.08132 -0.0104 1.0000 0.2642
-6.000 -0.5329 0.08521 0.07927 -0.0095 1.0000 0.2815
-5.750 -0.5265 0.08190 0.07597 -0.0049 1.0000 0.3059
-5.500 -0.5274 0.07912 0.07325 -0.0014 1.0000 0.3321
-5.250 -0.5301 0.07660 0.07079 0.0024 1.0000 0.3633
-5.000 -0.5298 0.07391 0.06817 0.0075 1.0000 0.3993
-4.500 -0.2246 0.05538 0.04875 0.0021 1.0000 0.8932
-4.250 -0.2605 0.05525 0.04881 0.0100 1.0000 0.8629
-4.000 -0.3047 0.05516 0.04893 0.0185 1.0000 0.8234
-3.750 -0.3498 0.05489 0.04887 0.0266 1.0000 0.7920
-3.500 -0.3956 0.05426 0.04845 0.0344 1.0000 0.7638
-3.250 -0.4000 0.04435 0.03655 -0.0235 1.0000 0.2286
-3.000 -0.3611 0.04019 0.03127 -0.0255 1.0000 0.1680
-2.750 -0.3349 0.03722 0.02772 -0.0248 1.0000 0.1522
-2.500 -0.3083 0.03474 0.02455 -0.0237 1.0000 0.1391
-2.250 -0.2832 0.03253 0.02178 -0.0225 1.0000 0.1329
-2.000 -0.2579 0.03075 0.01948 -0.0212 1.0000 0.1314
-1.750 -0.2340 0.02939 0.01780 -0.0201 1.0000 0.1398
-1.500 -0.2067 0.02791 0.01602 -0.0194 1.0000 0.1447
-1.250 -0.1785 0.02674 0.01465 -0.0188 1.0000 0.1529
-1.000 -0.1484 0.02574 0.01360 -0.0189 1.0000 0.1780
-0.750 -0.1205 0.02483 0.01265 -0.0185 1.0000 0.2063
-0.500 -0.0510 0.02157 0.01153 -0.0253 1.0000 1.0000
-0.250 -0.0306 0.02183 0.01131 -0.0241 1.0000 1.0000
0.000 -0.0104 0.02210 0.01125 -0.0231 1.0000 1.0000
0.250 0.0097 0.02240 0.01127 -0.0221 1.0000 1.0000
0.500 0.0297 0.02272 0.01133 -0.0211 1.0000 1.0000
0.750 0.0496 0.02306 0.01147 -0.0202 1.0000 1.0000
1.000 0.0695 0.02343 0.01168 -0.0193 1.0000 1.0000
1.250 0.0893 0.02381 0.01193 -0.0185 1.0000 1.0000
1.500 0.1090 0.02422 0.01223 -0.0177 1.0000 1.0000
1.750 0.1286 0.02465 0.01257 -0.0169 1.0000 1.0000
2.000 0.1480 0.02511 0.01297 -0.0161 1.0000 1.0000
2.250 0.1673 0.02560 0.01342 -0.0153 1.0000 1.0000
2.500 0.1865 0.02612 0.01392 -0.0146 1.0000 1.0000
2.750 0.2054 0.02667 0.01447 -0.0139 1.0000 1.0000
3.000 0.2241 0.02725 0.01509 -0.0132 1.0000 1.0000
3.250 0.2426 0.02787 0.01575 -0.0126 1.0000 1.0000
3.500 0.2607 0.02854 0.01648 -0.0119 1.0000 1.0000
3.750 0.2786 0.02925 0.01727 -0.0114 1.0000 1.0000
4.000 0.2960 0.03001 0.01813 -0.0108 1.0000 1.0000
4.250 0.3130 0.03084 0.01912 -0.0103 1.0000 1.0000
4.500 0.3295 0.03173 0.02014 -0.0098 1.0000 1.0000
4.750 0.3453 0.03270 0.02127 -0.0094 1.0000 1.0000
5.000 0.3607 0.03375 0.02249 -0.0090 1.0000 1.0000
5.250 0.3752 0.03491 0.02382 -0.0087 1.0000 1.0000
5.500 0.4097 0.03681 0.02605 -0.0128 0.9890 1.0000
5.750 0.7398 0.02803 0.01572 -0.0370 0.1644 1.0000
6.000 0.8395 0.03235 0.01995 -0.0482 0.1184 1.0000
6.250 0.9036 0.03693 0.02469 -0.0538 0.1096 1.0000
6.500 0.9288 0.03943 0.02785 -0.0521 0.1053 1.0000
6.750 0.9518 0.04241 0.03130 -0.0504 0.1016 1.0000
7.000 0.9720 0.04602 0.03547 -0.0482 0.1041 1.0000
7.250 0.9886 0.05000 0.03988 -0.0457 0.1075 1.0000
7.500 0.9970 0.05341 0.04403 -0.0415 0.1144 1.0000
7.750 1.0107 0.05852 0.04943 -0.0394 0.1222 1.0000
8.000 1.0129 0.06282 0.05436 -0.0352 0.1354 1.0000
8.250 0.9990 0.06671 0.05908 -0.0299 0.1563 1.0000
8.500 0.9843 0.07227 0.06518 -0.0267 0.1858 1.0000
8.750 0.9554 0.07811 0.07142 -0.0249 0.2226 1.0000
9.000 0.9190 0.08262 0.07602 -0.0227 0.2374 1.0000
9.250 0.8788 0.08816 0.08154 -0.0231 0.2516 1.0000
9.500 0.8280 0.09727 0.09051 -0.0306 0.2821 1.0000
9.750 0.7517 0.08785 0.08146 -0.0113 0.1967 1.0000
10.000 0.7526 0.11481 0.10770 -0.0485 0.4016 1.0000
10.250 0.7666 0.11944 0.11233 -0.0475 0.3835 1.0000
10.500 0.7582 0.12219 0.11503 -0.0466 0.3621 1.0000
10.750 0.7634 0.12608 0.11892 -0.0460 0.3469 1.0000
11.000 0.6314 0.12559 0.11888 -0.0352 0.3416 1.0000
11.250 0.6283 0.12864 0.12192 -0.0349 0.3267 1.0000
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Polar data table (+)
Polar graphs
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