GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 57 AIRFOIL (goe57-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.28 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe57-il-1000000.txt Download as CSV file: xf-goe57-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 57 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3137 0.09869 0.09711 -0.0245 1.0000 0.0138
-8.250 -0.3118 0.09599 0.09444 -0.0252 1.0000 0.0154
-8.000 -0.3157 0.09371 0.09219 -0.0248 1.0000 0.0155
-5.750 -0.0973 0.05289 0.05109 -0.0840 0.9301 0.0206
-5.500 -0.0778 0.05137 0.04950 -0.0844 0.9156 0.0210
-5.250 -0.0551 0.04965 0.04770 -0.0861 0.9016 0.0218
-5.000 -0.0284 0.04719 0.04513 -0.0892 0.8874 0.0233
-4.750 0.0157 0.04328 0.04101 -0.0965 0.8739 0.0255
-4.500 0.0523 0.02236 0.02002 -0.0943 0.8397 0.0257
-4.250 0.0770 0.01644 0.01393 -0.0993 0.8325 0.0266
-4.000 0.1009 0.01499 0.01240 -0.1002 0.8247 0.0271
-3.750 0.1260 0.01361 0.01094 -0.1012 0.8160 0.0278
-3.500 0.1527 0.01212 0.00934 -0.1025 0.8079 0.0289
-3.250 0.1856 0.01118 0.00822 -0.1036 0.7990 0.0326
-3.000 0.2215 0.02489 0.02159 -0.1105 0.8083 0.0329
-2.750 0.2509 0.02244 0.01890 -0.1113 0.7974 0.0330
-2.500 0.2798 0.02020 0.01642 -0.1120 0.7857 0.0331
-2.000 0.3373 0.01327 0.00866 -0.1137 0.7615 0.0337
-1.750 0.3650 0.01193 0.00711 -0.1137 0.7454 0.0323
-1.500 0.3922 0.01145 0.00643 -0.1134 0.7239 0.0328
-0.750 0.4724 0.00967 0.00392 -0.1125 0.6394 0.0333
-0.500 0.4990 0.00914 0.00319 -0.1122 0.6131 0.0334
-0.250 0.5257 0.00854 0.00242 -0.1120 0.5883 0.0346
0.000 0.5523 0.00837 0.00212 -0.1117 0.5600 0.0355
0.250 0.5787 0.00838 0.00199 -0.1113 0.5233 0.0367
0.500 0.6043 0.00854 0.00194 -0.1109 0.4741 0.0382
0.750 0.6297 0.00875 0.00192 -0.1104 0.4230 0.0395
1.000 0.6557 0.00891 0.00190 -0.1101 0.3854 0.0407
1.250 0.6818 0.00907 0.00191 -0.1097 0.3512 0.0418
1.500 0.7078 0.00929 0.00197 -0.1094 0.3165 0.0427
1.750 0.7337 0.00942 0.00191 -0.1091 0.2767 0.0482
2.000 0.7580 0.00986 0.00207 -0.1085 0.2166 0.0532
2.250 0.7840 0.01008 0.00218 -0.1082 0.1924 0.0621
2.500 0.8107 0.01019 0.00229 -0.1079 0.1840 0.0823
2.750 0.8378 0.01016 0.00245 -0.1079 0.1805 0.1816
3.000 0.8606 0.00882 0.00275 -0.1073 0.1771 1.0000
3.250 0.8870 0.00904 0.00290 -0.1070 0.1706 1.0000
3.500 0.9140 0.00917 0.00300 -0.1068 0.1669 1.0000
3.750 0.9408 0.00934 0.00313 -0.1066 0.1643 1.0000
4.000 0.9673 0.00952 0.00328 -0.1063 0.1612 1.0000
4.250 0.9934 0.00976 0.00348 -0.1060 0.1563 1.0000
4.500 1.0205 0.00985 0.00358 -0.1059 0.1543 1.0000
4.750 1.0472 0.00999 0.00371 -0.1057 0.1506 1.0000
5.000 1.0731 0.01023 0.00388 -0.1054 0.1419 1.0000
5.250 1.0991 0.01044 0.00398 -0.1051 0.1249 1.0000
5.500 1.1150 0.01198 0.00494 -0.1033 0.0199 1.0000
5.750 1.1402 0.01230 0.00527 -0.1028 0.0158 1.0000
6.000 1.1653 0.01262 0.00563 -0.1023 0.0148 1.0000
6.250 1.1899 0.01299 0.00606 -0.1017 0.0137 1.0000
6.500 1.2136 0.01348 0.00660 -0.1010 0.0124 1.0000
6.750 1.2361 0.01412 0.00732 -0.1001 0.0114 1.0000
7.000 1.2600 0.01455 0.00778 -0.0994 0.0110 1.0000
7.250 1.2832 0.01505 0.00833 -0.0986 0.0106 1.0000
7.500 1.3058 0.01560 0.00894 -0.0978 0.0101 1.0000
7.750 1.3278 0.01621 0.00960 -0.0968 0.0096 1.0000
8.000 1.3489 0.01689 0.01033 -0.0958 0.0092 1.0000
8.250 1.3685 0.01768 0.01117 -0.0945 0.0087 1.0000
8.500 1.3791 0.01936 0.01297 -0.0919 0.0082 1.0000
8.750 1.3968 0.02021 0.01389 -0.0904 0.0079 1.0000
9.000 1.4153 0.02093 0.01467 -0.0890 0.0077 1.0000
9.250 1.4315 0.02182 0.01562 -0.0873 0.0075 1.0000
9.500 1.4460 0.02281 0.01668 -0.0853 0.0073 1.0000
9.750 1.4589 0.02387 0.01781 -0.0832 0.0071 1.0000
10.000 1.4692 0.02496 0.01899 -0.0806 0.0070 1.0000
10.250 1.4768 0.02611 0.02021 -0.0776 0.0068 1.0000
10.500 1.4840 0.02731 0.02147 -0.0747 0.0067 1.0000
10.750 1.4907 0.02860 0.02284 -0.0720 0.0065 1.0000
11.000 1.4968 0.02999 0.02430 -0.0694 0.0064 1.0000
11.250 1.5028 0.03143 0.02580 -0.0671 0.0062 1.0000
11.500 1.5081 0.03300 0.02744 -0.0649 0.0061 1.0000
11.750 1.5124 0.03473 0.02924 -0.0628 0.0059 1.0000
12.000 1.5156 0.03669 0.03129 -0.0608 0.0058 1.0000
12.250 1.5177 0.03896 0.03363 -0.0588 0.0057 1.0000
12.500 1.5200 0.04157 0.03632 -0.0567 0.0056 1.0000
12.750 1.5267 0.04542 0.04027 -0.0543 0.0055 1.0000
13.000 1.5197 0.04823 0.04329 -0.0524 0.0054 1.0000
13.250 1.5153 0.05057 0.04578 -0.0513 0.0053 1.0000
13.500 1.5117 0.05337 0.04873 -0.0504 0.0052 1.0000
13.750 1.5067 0.05662 0.05213 -0.0496 0.0052 1.0000
14.000 1.5001 0.06036 0.05602 -0.0489 0.0052 1.0000
14.250 1.4917 0.06438 0.06020 -0.0487 0.0052 1.0000
14.500 1.4811 0.06886 0.06484 -0.0488 0.0052 1.0000
14.750 1.4696 0.07361 0.06975 -0.0494 0.0052 1.0000
15.000 1.4556 0.07894 0.07524 -0.0502 0.0052 1.0000
15.250 1.4536 0.08288 0.07936 -0.0506 0.0059 1.0000
15.500 1.4456 0.08750 0.08409 -0.0520 0.0059 1.0000
15.750 1.4364 0.09247 0.08914 -0.0539 0.0058 1.0000
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