GOE 5K AIRFOIL (goe05k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 5K AIRFOIL (goe05k-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.14 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe05k-il-1000000.txt Download as CSV file: xf-goe05k-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 5K 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 -0.4275 0.08340 0.08186 -0.0143 1.0000 0.0026
-8.250 -0.4278 0.07976 0.07823 -0.0148 1.0000 0.0026
-8.000 -0.4287 0.07622 0.07471 -0.0152 1.0000 0.0027
-7.750 -0.4302 0.07270 0.07120 -0.0156 1.0000 0.0027
-7.500 -0.4328 0.06933 0.06785 -0.0158 1.0000 0.0027
-7.250 -0.4377 0.06623 0.06478 -0.0157 1.0000 0.0027
-7.000 -0.4469 0.06361 0.06218 -0.0147 1.0000 0.0028
-6.750 -0.4522 0.06047 0.05906 -0.0154 1.0000 0.0028
-1.750 -0.0267 0.00881 0.00377 -0.0430 0.9803 0.0052
-1.500 0.0056 0.00815 0.00300 -0.0438 0.9794 0.0067
-1.250 0.0324 0.00728 0.00202 -0.0434 0.9766 0.0068
-1.000 0.0611 0.00678 0.00144 -0.0435 0.9738 0.0158
-0.750 0.1114 0.00418 0.00168 -0.0499 0.9816 1.0000
-0.500 0.1471 0.00415 0.00157 -0.0519 0.9802 1.0000
-0.250 0.1850 0.00410 0.00146 -0.0543 0.9790 1.0000
0.000 0.2189 0.00395 0.00129 -0.0557 0.9731 1.0000
0.250 0.2612 0.00379 0.00113 -0.0590 0.9697 1.0000
0.500 0.2956 0.00364 0.00099 -0.0605 0.9609 1.0000
0.750 0.3330 0.00350 0.00088 -0.0626 0.9482 1.0000
1.250 0.3884 0.00421 0.00067 -0.0619 0.6811 1.0000
1.500 0.3847 0.00664 0.00109 -0.0560 0.1342 1.0000
1.750 0.4028 0.00761 0.00169 -0.0538 0.0073 1.0000
2.000 0.4247 0.00818 0.00235 -0.0523 0.0047 1.0000
2.250 0.4433 0.00926 0.00351 -0.0501 0.0051 1.0000
4.500 0.6158 0.01130 0.00783 -0.0295 0.0032 1.0000
4.750 0.6354 0.01398 0.01078 -0.0270 0.0029 1.0000
5.000 0.6521 0.01716 0.01421 -0.0248 0.0026 1.0000
5.250 0.6673 0.02066 0.01793 -0.0229 0.0024 1.0000
5.500 0.6809 0.02439 0.02186 -0.0212 0.0023 1.0000
5.750 0.6910 0.02848 0.02611 -0.0199 0.0021 1.0000
6.000 0.6960 0.03376 0.03156 -0.0186 0.0021 1.0000
6.250 0.7054 0.03849 0.03646 -0.0172 0.0021 1.0000
6.500 0.7130 0.04333 0.04143 -0.0162 0.0021 1.0000
6.750 0.7181 0.04838 0.04661 -0.0154 0.0020 1.0000
7.000 0.7204 0.05337 0.05171 -0.0150 0.0020 1.0000
7.250 0.7195 0.05829 0.05671 -0.0148 0.0020 1.0000
7.500 0.7150 0.06322 0.06171 -0.0151 0.0020 1.0000
7.750 0.7036 0.06724 0.06577 -0.0147 0.0020 1.0000
8.000 0.6882 0.07145 0.07001 -0.0158 0.0020 1.0000
8.250 0.6742 0.07667 0.07523 -0.0201 0.0020 1.0000
8.500 0.6668 0.08189 0.08044 -0.0230 0.0021 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 5K AIRFOIL (goe05k-il)