GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 9K AIRFOIL (goe09k-il) Reynolds number: 500,000 Max Cl/Cd: 60.55 at α=1° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe09k-il-500000-n5.txt Download as CSV file: xf-goe09k-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 9K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4903 0.08392 0.08177 0.0007 1.0000 0.0036
-8.000 -0.4899 0.08007 0.07793 -0.0004 1.0000 0.0036
-7.750 -0.4903 0.07616 0.07404 -0.0014 1.0000 0.0038
-7.500 -0.4910 0.07238 0.07028 -0.0024 1.0000 0.0038
-7.000 -0.5686 0.07993 0.07775 -0.0046 1.0000 0.0033
-6.750 -0.5631 0.07609 0.07390 -0.0065 1.0000 0.0035
-6.500 -0.5520 0.07194 0.06974 -0.0100 1.0000 0.0036
-6.250 -0.5393 0.06761 0.06537 -0.0135 1.0000 0.0037
-6.000 -0.5242 0.06329 0.06101 -0.0168 1.0000 0.0039
-5.750 -0.5072 0.05884 0.05649 -0.0199 1.0000 0.0040
-5.500 -0.4885 0.05449 0.05205 -0.0224 1.0000 0.0042
-5.250 -0.4683 0.05012 0.04755 -0.0245 1.0000 0.0044
-5.000 -0.4462 0.04584 0.04313 -0.0261 1.0000 0.0047
-4.750 -0.4208 0.04157 0.03866 -0.0270 1.0000 0.0049
-4.500 -0.3966 0.03765 0.03454 -0.0271 1.0000 0.0050
-4.250 -0.3730 0.03394 0.03060 -0.0268 1.0000 0.0050
-4.000 -0.3552 0.03021 0.02667 -0.0268 1.0000 0.0053
-3.750 -0.3337 0.02727 0.02350 -0.0263 1.0000 0.0057
-3.500 -0.3102 0.02435 0.02030 -0.0254 1.0000 0.0062
-3.250 -0.2834 0.02172 0.01728 -0.0236 1.0000 0.0072
-3.000 -0.2598 0.01880 0.01397 -0.0224 1.0000 0.0074
-2.750 -0.2368 0.01646 0.01137 -0.0215 1.0000 0.0078
-2.500 -0.2107 0.01375 0.00830 -0.0199 1.0000 0.0030
-2.250 -0.1853 0.01186 0.00610 -0.0187 1.0000 0.0026
-2.000 -0.1601 0.01037 0.00435 -0.0175 1.0000 0.0025
-1.750 -0.1355 0.00925 0.00304 -0.0165 1.0000 0.0026
-1.500 -0.1110 0.00853 0.00220 -0.0156 1.0000 0.0037
-1.250 -0.0863 0.00800 0.00156 -0.0148 1.0000 0.0060
-1.000 -0.0590 0.00758 0.00111 -0.0147 0.9993 0.0246
-0.750 -0.0367 0.00562 0.00104 -0.0147 0.9983 0.6092
-0.500 0.0061 0.00461 0.00101 -0.0178 1.0000 1.0000
-0.250 0.0343 0.00464 0.00097 -0.0180 0.9990 1.0000
0.000 0.0722 0.00468 0.00095 -0.0205 0.9952 1.0000
0.250 0.1121 0.00467 0.00092 -0.0233 0.9894 1.0000
0.500 0.1558 0.00461 0.00089 -0.0270 0.9793 1.0000
0.750 0.1950 0.00453 0.00086 -0.0296 0.9654 1.0000
1.000 0.2646 0.00437 0.00074 -0.0387 0.8978 1.0000
1.250 0.2712 0.00652 0.00089 -0.0340 0.3633 1.0000
1.500 0.2878 0.00820 0.00132 -0.0323 0.0097 1.0000
1.750 0.3122 0.00871 0.00193 -0.0314 0.0051 1.0000
2.000 0.3365 0.00929 0.00260 -0.0305 0.0030 1.0000
2.250 0.3597 0.01021 0.00368 -0.0292 0.0027 1.0000
2.500 0.3830 0.01145 0.00507 -0.0278 0.0028 1.0000
2.750 0.4075 0.01301 0.00682 -0.0265 0.0030 1.0000
7.250 0.7391 0.08060 0.07843 -0.0230 0.0026 1.0000
7.750 0.7422 0.08933 0.08718 -0.0293 0.0027 1.0000
8.000 0.7385 0.09339 0.09121 -0.0321 0.0026 1.0000
8.250 0.7378 0.09744 0.09524 -0.0344 0.0025 1.0000
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Polar data table (+)
Polar graphs
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