GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 9K AIRFOIL (goe09k-il) Reynolds number: 500,000 Max Cl/Cd: 79.36 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe09k-il-500000.txt Download as CSV file: xf-goe09k-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5842 0.09487 0.09258 0.0059 1.0000 0.0046
-7.750 -0.5814 0.09164 0.08940 0.0026 1.0000 0.0050
-7.500 -0.5801 0.08829 0.08609 0.0000 1.0000 0.0050
-7.250 -0.5723 0.08425 0.08206 -0.0039 1.0000 0.0050
-7.000 -0.5635 0.08021 0.07802 -0.0072 1.0000 0.0050
-6.750 -0.5623 0.07615 0.07396 -0.0070 1.0000 0.0053
-6.500 -0.5515 0.07207 0.06987 -0.0103 1.0000 0.0054
-6.250 -0.5391 0.06778 0.06555 -0.0136 1.0000 0.0057
-6.000 -0.5240 0.06348 0.06121 -0.0169 1.0000 0.0059
-5.750 -0.5069 0.05904 0.05670 -0.0200 1.0000 0.0062
-5.500 -0.4880 0.05469 0.05225 -0.0226 1.0000 0.0065
-5.250 -0.4657 0.05026 0.04768 -0.0248 1.0000 0.0069
-5.000 -0.4387 0.04590 0.04314 -0.0265 1.0000 0.0072
-4.750 -0.3936 0.02412 0.02145 -0.0272 1.0000 0.0075
-4.500 -0.3782 0.02068 0.01789 -0.0276 1.0000 0.0081
-4.250 -0.3581 0.01745 0.01447 -0.0277 1.0000 0.0087
-4.000 -0.3351 0.01458 0.01134 -0.0273 1.0000 0.0097
-3.750 -0.3085 0.01267 0.00901 -0.0259 1.0000 0.0102
-3.500 -0.2931 0.00940 0.00561 -0.0261 1.0000 0.0113
-3.250 -0.2696 0.00786 0.00379 -0.0249 1.0000 0.0135
-3.000 -0.2473 0.00575 0.00131 -0.0239 1.0000 0.0153
-2.750 -0.2250 0.00470 0.00006 -0.0230 1.0000 0.0185
-1.750 -0.1364 0.01005 0.00395 -0.0170 1.0000 0.0088
-1.500 -0.1117 0.00898 0.00277 -0.0159 1.0000 0.0089
-1.250 -0.0870 0.00814 0.00184 -0.0150 1.0000 0.0119
-1.000 -0.0621 0.00745 0.00117 -0.0141 1.0000 0.0584
-0.750 -0.0173 0.00458 0.00108 -0.0187 1.0000 1.0000
-0.500 0.0061 0.00461 0.00101 -0.0178 1.0000 1.0000
-0.250 0.0296 0.00464 0.00098 -0.0170 1.0000 1.0000
0.000 0.0530 0.00469 0.00097 -0.0161 1.0000 1.0000
0.250 0.0761 0.00475 0.00101 -0.0153 1.0000 1.0000
0.500 0.0993 0.00482 0.00107 -0.0144 1.0000 1.0000
0.750 0.1221 0.00490 0.00118 -0.0135 1.0000 1.0000
1.000 0.1569 0.00497 0.00130 -0.0153 0.9974 1.0000
1.250 0.2202 0.00490 0.00138 -0.0233 0.9855 1.0000
1.500 0.2882 0.00818 0.00141 -0.0322 0.0164 1.0000
1.750 0.3118 0.00897 0.00232 -0.0310 0.0106 1.0000
2.000 0.3355 0.00975 0.00314 -0.0298 0.0080 1.0000
2.250 0.3580 0.01121 0.00475 -0.0281 0.0099 1.0000
3.250 0.4444 0.00560 0.00050 -0.0199 0.0183 1.0000
3.500 0.4661 0.00691 0.00195 -0.0192 0.0152 1.0000
3.750 0.4894 0.00866 0.00419 -0.0174 0.0128 1.0000
4.000 0.5102 0.01055 0.00631 -0.0164 0.0110 1.0000
4.250 0.5267 0.01415 0.01018 -0.0154 0.0103 1.0000
4.500 0.5526 0.01637 0.01282 -0.0133 0.0089 1.0000
4.750 0.5688 0.01966 0.01630 -0.0128 0.0077 1.0000
5.000 0.5860 0.02418 0.02110 -0.0118 0.0072 1.0000
5.250 0.6071 0.02828 0.02547 -0.0110 0.0062 1.0000
5.500 0.6223 0.03285 0.03022 -0.0109 0.0057 1.0000
5.750 0.6328 0.03751 0.03500 -0.0111 0.0053 1.0000
6.000 0.6787 0.05688 0.05422 -0.0124 0.0051 1.0000
6.250 0.6960 0.06155 0.05906 -0.0133 0.0051 1.0000
6.500 0.7119 0.06643 0.06407 -0.0151 0.0049 1.0000
6.750 0.7236 0.07128 0.06901 -0.0173 0.0048 1.0000
7.000 0.7324 0.07613 0.07393 -0.0199 0.0046 1.0000
7.250 0.7386 0.08081 0.07865 -0.0229 0.0045 1.0000
7.500 0.7424 0.08532 0.08318 -0.0261 0.0045 1.0000
7.750 0.7417 0.08951 0.08737 -0.0292 0.0045 1.0000
8.000 0.7382 0.09358 0.09141 -0.0320 0.0044 1.0000
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Polar data table (+)
Polar graphs
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