GOE 458 AIRFOIL (goe458-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 458 AIRFOIL (goe458-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.29 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe458-il-1000000-n5.txt Download as CSV file: xf-goe458-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 458 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3151 0.13132 0.12964 -0.0321 1.0000 0.0016
-11.000 -0.3112 0.12832 0.12666 -0.0325 1.0000 0.0016
-10.750 -0.3092 0.12492 0.12327 -0.0327 1.0000 0.0014
-10.500 -0.3050 0.12109 0.11946 -0.0337 0.9998 0.0014
-10.250 -0.2935 0.11708 0.11546 -0.0367 0.9989 0.0013
-10.000 -0.2815 0.11304 0.11141 -0.0398 0.9972 0.0013
-9.750 -0.2720 0.10901 0.10739 -0.0422 0.9930 0.0013
-9.500 -0.2595 0.10539 0.10378 -0.0450 0.9890 0.0015
-9.250 -0.2499 0.10146 0.09985 -0.0477 0.9836 0.0015
-9.000 -0.2378 0.09746 0.09586 -0.0509 0.9784 0.0015
-8.750 -0.2262 0.09375 0.09215 -0.0546 0.9722 0.0022
-8.500 -0.2100 0.08912 0.08751 -0.0596 0.9670 0.0021
-8.250 -0.1893 0.08633 0.08471 -0.0639 0.9611 0.0025
-8.000 -0.1652 0.08124 0.07959 -0.0712 0.9553 0.0024
-7.750 -0.1376 0.07770 0.07601 -0.0779 0.9465 0.0030
-7.500 -0.1128 0.07341 0.07168 -0.0849 0.9338 0.0033
-7.250 -0.0973 0.06956 0.06775 -0.0895 0.9140 0.0031
-7.000 -0.0875 0.06743 0.06556 -0.0912 0.8957 0.0044
-6.750 -0.0786 0.06449 0.06255 -0.0936 0.8798 0.0048
-6.500 -0.0688 0.06132 0.05933 -0.0962 0.8668 0.0049
-6.250 -0.0577 0.05795 0.05592 -0.0993 0.8550 0.0047
-6.000 -0.0436 0.05452 0.05242 -0.1027 0.8441 0.0047
-5.750 -0.0273 0.05050 0.04832 -0.1068 0.8345 0.0044
-5.500 -0.0076 0.04633 0.04409 -0.1112 0.8254 0.0042
-5.250 0.0149 0.04170 0.03936 -0.1159 0.8171 0.0040
-5.000 0.0402 0.03642 0.03394 -0.1206 0.8089 0.0038
-4.750 0.0675 0.03046 0.02777 -0.1249 0.8009 0.0036
-4.500 0.0941 0.02219 0.01904 -0.1281 0.7936 0.0033
-4.250 0.1184 0.01694 0.01317 -0.1286 0.7858 0.0031
-4.000 0.1430 0.01360 0.00925 -0.1281 0.7784 0.0030
-3.750 0.1684 0.01105 0.00619 -0.1274 0.7702 0.0030
-3.500 0.1938 0.00914 0.00386 -0.1265 0.7616 0.0037
-3.250 0.2205 0.00889 0.00349 -0.1262 0.7514 0.0054
-3.000 0.2475 0.00890 0.00342 -0.1260 0.7399 0.0061
-2.750 0.2748 0.00911 0.00357 -0.1259 0.7274 0.0064
-2.500 0.3005 0.00862 0.00299 -0.1257 0.7147 0.0081
-2.250 0.3267 0.00818 0.00241 -0.1253 0.7011 0.0084
-2.000 0.3529 0.00788 0.00198 -0.1249 0.6867 0.0096
-1.750 0.3793 0.00779 0.00180 -0.1246 0.6726 0.0130
-1.500 0.4059 0.00778 0.00172 -0.1243 0.6596 0.0144
-1.250 0.4327 0.00782 0.00172 -0.1241 0.6485 0.0152
-1.000 0.4591 0.00762 0.00142 -0.1239 0.6382 0.0166
-0.750 0.4853 0.00749 0.00115 -0.1236 0.6252 0.0191
-0.500 0.5116 0.00751 0.00108 -0.1233 0.6108 0.0185
-0.250 0.5380 0.00753 0.00102 -0.1230 0.5978 0.0180
0.000 0.5645 0.00755 0.00098 -0.1227 0.5866 0.0176
0.250 0.5912 0.00757 0.00094 -0.1225 0.5759 0.0172
0.500 0.6180 0.00760 0.00092 -0.1223 0.5662 0.0169
0.750 0.6447 0.00763 0.00091 -0.1222 0.5582 0.0167
1.000 0.6714 0.00767 0.00091 -0.1220 0.5489 0.0166
1.250 0.6979 0.00772 0.00092 -0.1218 0.5381 0.0166
1.500 0.7241 0.00779 0.00095 -0.1215 0.5240 0.0169
1.750 0.7500 0.00770 0.00103 -0.1213 0.5120 0.1145
2.000 0.7760 0.00760 0.00117 -0.1211 0.5034 0.2089
2.250 0.8024 0.00756 0.00128 -0.1210 0.4954 0.2738
2.500 0.8329 0.00628 0.00156 -0.1222 0.4867 1.0000
2.750 0.8588 0.00640 0.00164 -0.1219 0.4767 1.0000
3.000 0.8849 0.00652 0.00174 -0.1217 0.4654 1.0000
3.250 0.9104 0.00668 0.00184 -0.1213 0.4512 1.0000
3.500 0.9274 0.00751 0.00223 -0.1195 0.3492 1.0000
3.750 0.9415 0.00867 0.00278 -0.1173 0.2310 1.0000
4.000 0.9491 0.01045 0.00366 -0.1141 0.0569 1.0000
4.250 0.9693 0.01110 0.00414 -0.1127 0.0028 1.0000
4.500 0.9935 0.01137 0.00443 -0.1121 0.0020 1.0000
4.750 1.0168 0.01172 0.00485 -0.1113 0.0016 1.0000
5.000 1.0392 0.01215 0.00535 -0.1102 0.0015 1.0000
5.250 1.0606 0.01267 0.00594 -0.1090 0.0015 1.0000
5.500 1.0807 0.01332 0.00668 -0.1076 0.0015 1.0000
5.750 1.0994 0.01406 0.00751 -0.1059 0.0015 1.0000
6.000 1.1164 0.01492 0.00846 -0.1039 0.0015 1.0000
6.250 1.1312 0.01591 0.00955 -0.1015 0.0016 1.0000
6.500 1.1438 0.01708 0.01089 -0.0987 0.0017 1.0000
6.750 1.1561 0.01834 0.01223 -0.0959 0.0018 1.0000
7.000 1.1701 0.01966 0.01362 -0.0935 0.0019 1.0000
7.250 1.1872 0.02126 0.01529 -0.0916 0.0020 1.0000
7.500 1.2096 0.02319 0.01730 -0.0906 0.0021 1.0000
7.750 1.2353 0.02537 0.01959 -0.0902 0.0023 1.0000
8.000 1.2656 0.03114 0.02561 -0.0906 0.0029 1.0000
8.250 1.2837 0.03390 0.02856 -0.0891 0.0029 1.0000
8.500 1.2982 0.03655 0.03144 -0.0870 0.0029 1.0000
8.750 1.3096 0.03922 0.03433 -0.0847 0.0029 1.0000
9.000 1.3182 0.04192 0.03726 -0.0820 0.0029 1.0000
9.250 1.3237 0.04468 0.04025 -0.0790 0.0029 1.0000
9.500 1.3258 0.04752 0.04331 -0.0758 0.0029 1.0000
9.750 1.3245 0.05029 0.04629 -0.0723 0.0029 1.0000
10.000 1.3185 0.05301 0.04922 -0.0683 0.0029 1.0000
10.250 1.3068 0.05538 0.05175 -0.0635 0.0029 1.0000
10.500 1.2933 0.05792 0.05445 -0.0592 0.0029 1.0000
10.750 1.2787 0.06077 0.05746 -0.0556 0.0029 1.0000
11.000 1.2637 0.06383 0.06068 -0.0528 0.0029 1.0000
11.250 1.2477 0.06725 0.06426 -0.0507 0.0029 1.0000
11.500 1.2307 0.07111 0.06827 -0.0494 0.0029 1.0000
11.750 1.2135 0.07533 0.07264 -0.0488 0.0029 1.0000
12.000 1.1954 0.08007 0.07751 -0.0491 0.0029 1.0000
12.250 1.1780 0.08510 0.08268 -0.0501 0.0029 1.0000
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Polar data table (+)
Polar graphs
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