GOE 444 AIRFOIL (goe444-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 444 AIRFOIL (goe444-il) Reynolds number: 500,000 Max Cl/Cd: 31.82 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe444-il-500000-n5.txt Download as CSV file: xf-goe444-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 444 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5293 0.09448 0.09235 0.0027 1.0000 0.0071
-9.250 -0.6285 0.09824 0.09604 0.0041 1.0000 0.0066
-9.000 -0.6285 0.09397 0.09179 0.0021 1.0000 0.0066
-8.750 -0.6291 0.08987 0.08771 0.0002 1.0000 0.0067
-8.500 -0.6302 0.08551 0.08337 -0.0025 1.0000 0.0067
-8.250 -0.6328 0.08141 0.07930 -0.0053 1.0000 0.0068
-8.000 -0.6411 0.07620 0.07410 -0.0099 1.0000 0.0068
-7.750 -0.6429 0.07181 0.06968 -0.0122 1.0000 0.0068
-7.500 -0.6423 0.06718 0.06499 -0.0141 1.0000 0.0069
-7.250 -0.6395 0.06293 0.06065 -0.0152 1.0000 0.0070
-7.000 -0.6348 0.05888 0.05650 -0.0158 1.0000 0.0072
-6.750 -0.6282 0.05467 0.05210 -0.0160 1.0000 0.0073
-6.500 -0.6196 0.05071 0.04799 -0.0157 1.0000 0.0075
-6.250 -0.6092 0.04691 0.04402 -0.0150 1.0000 0.0078
-6.000 -0.5971 0.04324 0.04015 -0.0139 1.0000 0.0082
-5.750 -0.5832 0.03979 0.03648 -0.0125 1.0000 0.0088
-5.500 -0.5663 0.03668 0.03312 -0.0107 1.0000 0.0095
-5.250 -0.5433 0.03508 0.03123 -0.0086 1.0000 0.0104
-5.000 -0.5264 0.03252 0.02838 -0.0066 1.0000 0.0105
-4.750 -0.5095 0.02990 0.02547 -0.0046 1.0000 0.0105
-4.500 -0.4920 0.02734 0.02262 -0.0026 1.0000 0.0106
-4.250 -0.4737 0.02491 0.01989 -0.0007 1.0000 0.0106
-3.750 -0.4363 0.01721 0.01154 0.0038 1.0000 0.0058
-3.500 -0.4144 0.01519 0.00928 0.0055 1.0000 0.0053
-3.250 -0.3918 0.01357 0.00746 0.0071 1.0000 0.0049
-3.000 -0.3697 0.01222 0.00597 0.0087 1.0000 0.0046
-2.750 -0.3487 0.01109 0.00470 0.0104 1.0000 0.0043
-2.500 -0.3242 0.01013 0.00347 0.0113 0.9992 0.0039
-2.250 -0.2928 0.00939 0.00260 0.0106 0.9965 0.0037
-2.000 -0.2608 0.00892 0.00200 0.0097 0.9935 0.0035
-1.750 -0.2277 0.00866 0.00163 0.0085 0.9897 0.0034
-1.500 -0.1925 0.00847 0.00136 0.0067 0.9858 0.0035
-1.250 -0.1592 0.00832 0.00117 0.0055 0.9798 0.0038
-1.000 -0.1259 0.00820 0.00104 0.0041 0.9740 0.0048
-0.750 -0.1009 0.00657 0.00089 0.0037 0.9664 0.4085
-0.500 -0.0882 0.00483 0.00100 0.0071 0.9554 0.8661
-0.250 -0.0447 0.00478 0.00109 0.0038 0.9499 0.9250
0.000 -0.0002 0.00478 0.00110 0.0000 0.9402 0.9400
0.250 0.0448 0.00478 0.00109 -0.0038 0.9247 0.9499
0.500 0.0883 0.00483 0.00100 -0.0071 0.8657 0.9554
0.750 0.1015 0.00649 0.00088 -0.0037 0.4274 0.9664
1.000 0.1258 0.00820 0.00105 -0.0041 0.0050 0.9739
1.250 0.1590 0.00832 0.00117 -0.0054 0.0039 0.9797
1.500 0.1924 0.00847 0.00136 -0.0067 0.0035 0.9856
1.750 0.2275 0.00865 0.00161 -0.0084 0.0035 0.9896
2.000 0.2606 0.00893 0.00201 -0.0096 0.0035 0.9933
2.250 0.2926 0.00937 0.00258 -0.0105 0.0037 0.9963
2.500 0.3239 0.01018 0.00352 -0.0112 0.0040 0.9990
2.750 0.3492 0.01112 0.00473 -0.0105 0.0043 1.0000
3.000 0.3704 0.01223 0.00598 -0.0088 0.0046 1.0000
3.250 0.3925 0.01358 0.00747 -0.0072 0.0049 1.0000
3.500 0.4150 0.01522 0.00931 -0.0056 0.0053 1.0000
3.750 0.4370 0.01709 0.01142 -0.0040 0.0057 1.0000
4.000 0.4550 0.02260 0.01731 -0.0013 0.0106 1.0000
4.250 0.4742 0.02489 0.01988 0.0006 0.0106 1.0000
4.500 0.4923 0.02743 0.02271 0.0026 0.0106 1.0000
4.750 0.5097 0.02994 0.02551 0.0046 0.0105 1.0000
5.000 0.5267 0.03249 0.02835 0.0066 0.0105 1.0000
5.250 0.5435 0.03505 0.03120 0.0086 0.0104 1.0000
5.500 0.5670 0.03661 0.03305 0.0107 0.0094 1.0000
5.750 0.5833 0.03974 0.03643 0.0125 0.0087 1.0000
6.000 0.5970 0.04324 0.04015 0.0139 0.0082 1.0000
6.250 0.6089 0.04699 0.04410 0.0150 0.0079 1.0000
6.500 0.6194 0.05064 0.04792 0.0157 0.0075 1.0000
6.750 0.6279 0.05463 0.05207 0.0160 0.0073 1.0000
7.000 0.6345 0.05874 0.05636 0.0159 0.0071 1.0000
7.250 0.6392 0.06278 0.06050 0.0154 0.0070 1.0000
7.500 0.6415 0.06727 0.06507 0.0142 0.0069 1.0000
7.750 0.6425 0.07162 0.06948 0.0124 0.0068 1.0000
8.000 0.6407 0.07603 0.07393 0.0102 0.0067 1.0000
8.250 0.6330 0.08100 0.07889 0.0059 0.0068 1.0000
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Polar data table (+)
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