GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 6K AIRFOIL (goe06k-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.63 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe06k-il-1000000.txt Download as CSV file: xf-goe06k-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3368 0.11597 0.11439 -0.0392 0.9956 0.0074
-11.000 -0.4779 0.12559 0.12396 -0.0219 1.0000 0.0067
-10.750 -0.4737 0.12148 0.11986 -0.0239 0.9996 0.0066
-10.500 -0.4627 0.11880 0.11717 -0.0260 0.9990 0.0072
-10.250 -0.4536 0.11494 0.11330 -0.0288 0.9982 0.0074
-10.000 -0.4446 0.11094 0.10930 -0.0318 0.9972 0.0076
-9.750 -0.4356 0.10696 0.10531 -0.0349 0.9963 0.0080
-9.500 -0.4257 0.10287 0.10123 -0.0383 0.9955 0.0087
-9.250 -0.4149 0.09861 0.09696 -0.0423 0.9947 0.0091
-9.000 -0.4061 0.09454 0.09290 -0.0463 0.9925 0.0096
-8.750 -0.3965 0.09040 0.08876 -0.0501 0.9905 0.0097
-8.500 -0.3868 0.08600 0.08437 -0.0544 0.9885 0.0097
-8.250 -0.3757 0.08151 0.07988 -0.0596 0.9868 0.0097
-8.000 -0.3638 0.07640 0.07477 -0.0670 0.9850 0.0097
-7.750 -0.3554 0.07157 0.06993 -0.0723 0.9794 0.0097
-7.500 -0.3386 0.06555 0.06386 -0.0798 0.9759 0.0098
-7.250 -0.3188 0.05988 0.05812 -0.0864 0.9740 0.0098
-7.000 -0.2975 0.05365 0.05178 -0.0927 0.9726 0.0098
-6.750 -0.2611 0.02774 0.02579 -0.0959 0.9630 0.0101
-5.750 -0.2385 0.02513 0.02200 -0.0952 0.9523 0.0089
-5.500 -0.2245 0.01835 0.01455 -0.0927 0.9499 0.0094
-5.000 -0.1727 0.01345 0.00885 -0.0925 0.9480 0.0100
-4.750 -0.1447 0.01148 0.00660 -0.0929 0.9472 0.0112
-4.500 -0.1274 0.01100 0.00605 -0.0907 0.9427 0.0118
-4.250 -0.1008 0.01042 0.00539 -0.0905 0.9404 0.0129
-4.000 -0.0706 0.00991 0.00481 -0.0911 0.9389 0.0141
-3.750 -0.0389 0.00943 0.00426 -0.0921 0.9377 0.0148
-3.500 -0.0092 0.00846 0.00315 -0.0927 0.9363 0.0172
-3.250 0.0244 0.00818 0.00286 -0.0942 0.9352 0.0198
-3.000 0.0587 0.00791 0.00256 -0.0958 0.9342 0.0222
-2.750 0.0788 0.00762 0.00221 -0.0941 0.9298 0.0249
-2.500 0.1069 0.00742 0.00202 -0.0943 0.9270 0.0315
-2.250 0.1377 0.00720 0.00182 -0.0951 0.9248 0.0401
-2.000 0.1709 0.00712 0.00173 -0.0965 0.9229 0.0457
-1.750 0.2048 0.00689 0.00151 -0.0980 0.9211 0.0571
-1.500 0.2280 0.00681 0.00141 -0.0971 0.9170 0.0638
-1.250 0.2545 0.00666 0.00132 -0.0969 0.9135 0.0797
-1.000 0.2774 0.00595 0.00125 -0.0963 0.9101 0.3071
-0.750 0.2957 0.00504 0.00124 -0.0947 0.9063 0.6193
-0.500 0.3005 0.00442 0.00130 -0.0894 0.8997 0.8343
-0.250 0.4224 0.00437 0.00155 -0.1114 0.9074 0.9577
0.000 0.4519 0.00449 0.00164 -0.1116 0.8990 0.9720
0.250 0.4935 0.00455 0.00166 -0.1147 0.8921 0.9770
0.500 0.5329 0.00467 0.00178 -0.1174 0.8860 0.9849
0.750 0.5816 0.00472 0.00179 -0.1222 0.8790 0.9889
1.000 0.6176 0.00476 0.00179 -0.1240 0.8646 0.9932
1.250 0.6579 0.00474 0.00175 -0.1269 0.8460 0.9968
1.500 0.6983 0.00473 0.00168 -0.1299 0.8258 1.0000
1.750 0.7083 0.00488 0.00164 -0.1258 0.7777 1.0000
2.000 0.7166 0.00514 0.00167 -0.1214 0.7252 1.0000
2.250 0.7195 0.00558 0.00178 -0.1158 0.6466 1.0000
2.500 0.7102 0.00659 0.00209 -0.1077 0.4853 1.0000
2.750 0.7140 0.00740 0.00237 -0.1027 0.3613 1.0000
3.000 0.7183 0.00827 0.00268 -0.0980 0.2293 1.0000
3.250 0.7274 0.00900 0.00298 -0.0942 0.1273 1.0000
3.500 0.7411 0.00953 0.00324 -0.0914 0.0685 1.0000
3.750 0.7602 0.00978 0.00345 -0.0896 0.0554 1.0000
4.000 0.7792 0.01003 0.00368 -0.0878 0.0412 1.0000
4.250 0.7967 0.01040 0.00394 -0.0856 0.0257 1.0000
4.500 0.8152 0.01071 0.00427 -0.0837 0.0206 1.0000
4.750 0.8340 0.01100 0.00457 -0.0818 0.0176 1.0000
5.000 0.8478 0.01169 0.00536 -0.0788 0.0143 1.0000
5.250 0.8667 0.01199 0.00570 -0.0770 0.0138 1.0000
5.500 0.8857 0.01230 0.00605 -0.0752 0.0126 1.0000
5.750 0.9034 0.01272 0.00652 -0.0731 0.0116 1.0000
6.000 0.9217 0.01310 0.00690 -0.0713 0.0105 1.0000
6.250 0.9335 0.01409 0.00799 -0.0680 0.0093 1.0000
6.500 0.9470 0.01552 0.00957 -0.0652 0.0089 1.0000
6.750 0.9668 0.01592 0.01002 -0.0637 0.0087 1.0000
7.000 0.9866 0.01663 0.01083 -0.0622 0.0084 1.0000
7.250 1.0066 0.01726 0.01153 -0.0607 0.0078 1.0000
7.500 1.0273 0.01827 0.01265 -0.0595 0.0074 1.0000
7.750 1.0470 0.01902 0.01349 -0.0581 0.0068 1.0000
8.000 1.0688 0.02073 0.01539 -0.0571 0.0067 1.0000
8.250 1.0868 0.02151 0.01626 -0.0554 0.0064 1.0000
8.500 1.1034 0.02258 0.01744 -0.0536 0.0060 1.0000
8.750 1.1180 0.02487 0.02000 -0.0515 0.0058 1.0000
9.000 1.1274 0.02779 0.02326 -0.0484 0.0057 1.0000
9.250 1.1286 0.03131 0.02717 -0.0439 0.0056 1.0000
9.500 1.1219 0.03514 0.03140 -0.0383 0.0056 1.0000
9.750 1.1287 0.03681 0.03325 -0.0349 0.0058 1.0000
10.000 1.1130 0.04032 0.03706 -0.0282 0.0057 1.0000
10.250 1.1005 0.04325 0.04024 -0.0222 0.0057 1.0000
10.500 1.0764 0.04715 0.04441 -0.0155 0.0057 1.0000
10.750 1.0540 0.05104 0.04852 -0.0099 0.0057 1.0000
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