GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 6K AIRFOIL (goe06k-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.82 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe06k-il-1000000-n5.txt Download as CSV file: xf-goe06k-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3882 0.12437 0.12262 -0.0456 0.9935 0.0031
-11.000 -0.3816 0.12041 0.11866 -0.0480 0.9927 0.0032
-10.750 -0.3745 0.11660 0.11486 -0.0501 0.9919 0.0032
-10.500 -0.3674 0.11267 0.11093 -0.0523 0.9911 0.0032
-10.250 -0.3591 0.10885 0.10712 -0.0548 0.9903 0.0032
-10.000 -0.3509 0.10498 0.10325 -0.0574 0.9896 0.0032
-9.750 -0.3436 0.10093 0.09921 -0.0600 0.9889 0.0032
-8.750 -0.3126 0.08623 0.08452 -0.0701 0.9829 0.0032
-8.500 -0.3045 0.08207 0.08037 -0.0736 0.9812 0.0032
-8.000 -0.2107 0.05488 0.05327 -0.0838 0.9704 0.0030
-7.500 -0.2689 0.06520 0.06350 -0.0921 0.9684 0.0029
-7.250 -0.2641 0.06120 0.05947 -0.0948 0.9601 0.0028
-7.000 -0.2470 0.05616 0.05437 -0.1005 0.9570 0.0026
-6.750 -0.2361 0.05112 0.04926 -0.1036 0.9501 0.0025
-6.500 -0.2180 0.04572 0.04373 -0.1073 0.9454 0.0024
-6.250 -0.1946 0.03906 0.03685 -0.1116 0.9425 0.0022
-6.000 -0.1759 0.03474 0.03233 -0.1125 0.9375 0.0024
-5.750 -0.1552 0.02971 0.02701 -0.1131 0.9329 0.0026
-5.500 -0.1309 0.02412 0.02102 -0.1137 0.9296 0.0026
-5.250 -0.1227 0.01438 0.01029 -0.1092 0.9232 0.0029
-5.000 -0.1007 0.01165 0.00699 -0.1079 0.9191 0.0031
-4.750 -0.0733 0.01024 0.00526 -0.1079 0.9162 0.0032
-4.500 -0.0444 0.00935 0.00418 -0.1084 0.9138 0.0033
-4.250 -0.0195 0.00893 0.00368 -0.1080 0.9105 0.0039
-4.000 0.0052 0.00853 0.00318 -0.1075 0.9070 0.0043
-3.750 0.0320 0.00817 0.00272 -0.1074 0.9037 0.0047
-3.500 0.0603 0.00785 0.00235 -0.1077 0.9008 0.0058
-3.250 0.0889 0.00758 0.00201 -0.1081 0.8981 0.0067
-3.000 0.1114 0.00735 0.00175 -0.1070 0.8943 0.0082
-2.750 0.1366 0.00715 0.00152 -0.1065 0.8909 0.0108
-2.500 0.1634 0.00698 0.00133 -0.1065 0.8878 0.0154
-2.250 0.1914 0.00681 0.00118 -0.1067 0.8850 0.0299
-2.000 0.2169 0.00671 0.00111 -0.1064 0.8818 0.0450
-1.750 0.2411 0.00661 0.00103 -0.1057 0.8780 0.0544
-1.500 0.2674 0.00654 0.00093 -0.1055 0.8745 0.0618
-1.250 0.2942 0.00640 0.00087 -0.1055 0.8714 0.0890
-1.000 0.3177 0.00609 0.00082 -0.1048 0.8682 0.1934
-0.750 0.3392 0.00583 0.00080 -0.1036 0.8642 0.2834
-0.500 0.3607 0.00549 0.00079 -0.1025 0.8601 0.4115
-0.250 0.3818 0.00508 0.00078 -0.1014 0.8556 0.5679
0.000 0.3970 0.00474 0.00080 -0.0986 0.8489 0.6931
0.250 0.4135 0.00443 0.00081 -0.0960 0.8418 0.8081
0.750 0.5543 0.00447 0.00120 -0.1163 0.8265 0.9769
1.000 0.5945 0.00462 0.00135 -0.1193 0.8151 0.9870
1.250 0.6309 0.00475 0.00138 -0.1214 0.7879 0.9908
1.500 0.6617 0.00503 0.00145 -0.1222 0.7389 0.9957
1.750 0.6900 0.00529 0.00153 -0.1226 0.6932 0.9985
2.000 0.7119 0.00562 0.00164 -0.1214 0.6344 1.0000
2.250 0.7053 0.00657 0.00194 -0.1140 0.4889 1.0000
2.500 0.7047 0.00755 0.00228 -0.1081 0.3386 1.0000
2.750 0.7056 0.00859 0.00265 -0.1026 0.1810 1.0000
3.000 0.7163 0.00924 0.00294 -0.0992 0.0889 1.0000
3.250 0.7333 0.00958 0.00317 -0.0970 0.0586 1.0000
3.500 0.7498 0.00998 0.00341 -0.0948 0.0235 1.0000
3.750 0.7680 0.01029 0.00369 -0.0928 0.0115 1.0000
4.000 0.7867 0.01056 0.00396 -0.0910 0.0077 1.0000
4.250 0.8058 0.01082 0.00425 -0.0892 0.0063 1.0000
4.500 0.8239 0.01117 0.00462 -0.0872 0.0051 1.0000
4.750 0.8431 0.01143 0.00492 -0.0855 0.0042 1.0000
5.000 0.8603 0.01185 0.00538 -0.0834 0.0037 1.0000
5.250 0.8777 0.01222 0.00580 -0.0813 0.0032 1.0000
5.500 0.8940 0.01265 0.00629 -0.0789 0.0030 1.0000
5.750 0.9102 0.01309 0.00679 -0.0766 0.0027 1.0000
6.000 0.9255 0.01364 0.00741 -0.0741 0.0026 1.0000
6.250 0.9403 0.01433 0.00817 -0.0715 0.0024 1.0000
6.500 0.9549 0.01528 0.00924 -0.0689 0.0023 1.0000
6.750 0.9735 0.01578 0.00984 -0.0672 0.0021 1.0000
7.000 0.9922 0.01680 0.01101 -0.0655 0.0019 1.0000
7.250 1.0114 0.01724 0.01153 -0.0641 0.0017 1.0000
7.500 1.0346 0.01882 0.01333 -0.0634 0.0016 1.0000
7.750 1.0568 0.02001 0.01469 -0.0626 0.0015 1.0000
8.000 1.0788 0.02198 0.01695 -0.0618 0.0015 1.0000
8.250 1.0862 0.03163 0.02766 -0.0567 0.0013 1.0000
8.500 1.0798 0.03845 0.03499 -0.0497 0.0013 1.0000
8.750 1.0727 0.04350 0.04037 -0.0435 0.0013 1.0000
9.000 1.0620 0.04840 0.04555 -0.0373 0.0013 1.0000
9.250 1.0535 0.05191 0.04926 -0.0321 0.0013 1.0000
9.500 1.0390 0.05536 0.05289 -0.0264 0.0013 1.0000
9.750 1.0199 0.05878 0.05647 -0.0201 0.0013 1.0000
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Polar data table (+)
Polar graphs
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