GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il) Reynolds number: 500,000 Max Cl/Cd: 110.46 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe610bm-il-500000.txt Download as CSV file: xf-goe610bm-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610-B MOD. 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3001 0.09570 0.09360 -0.0248 1.0000 0.0154
-7.500 -0.2945 0.09287 0.09081 -0.0261 1.0000 0.0160
-7.250 -0.2965 0.09080 0.08879 -0.0257 1.0000 0.0166
-7.000 -0.2700 0.08656 0.08455 -0.0377 0.9906 0.0176
-6.750 -0.2403 0.08160 0.07957 -0.0473 0.9835 0.0177
-6.500 -0.2144 0.07695 0.07490 -0.0544 0.9739 0.0178
-6.250 -0.1891 0.07234 0.07025 -0.0609 0.9633 0.0178
-6.000 -0.1768 0.06669 0.06458 -0.0641 0.9521 0.0182
-5.750 -0.1632 0.06391 0.06176 -0.0645 0.9405 0.0185
-5.500 -0.1456 0.06101 0.05881 -0.0665 0.9286 0.0190
-5.250 -0.1238 0.05782 0.05556 -0.0699 0.9172 0.0197
-5.000 -0.0974 0.05420 0.05186 -0.0746 0.9067 0.0211
-4.750 -0.0485 0.04932 0.04677 -0.0847 0.8972 0.0236
-4.500 -0.0133 0.04493 0.04220 -0.0898 0.8869 0.0238
-4.250 0.0204 0.04017 0.03723 -0.0942 0.8772 0.0239
-4.000 0.0438 0.03421 0.03110 -0.0982 0.8680 0.0252
-3.750 0.0700 0.03236 0.02915 -0.0995 0.8574 0.0264
-3.500 0.1012 0.02984 0.02644 -0.1015 0.8470 0.0291
-3.250 0.1406 0.02811 0.02425 -0.1027 0.8371 0.0326
-3.000 0.1736 0.02182 0.01750 -0.1064 0.8278 0.0347
-1.250 0.3851 0.01271 0.00648 -0.1098 0.7501 0.0466
-1.000 0.4139 0.01268 0.00631 -0.1096 0.7381 0.0449
-0.750 0.4432 0.01162 0.00511 -0.1098 0.7265 0.0435
-0.500 0.4722 0.01108 0.00447 -0.1100 0.7137 0.0434
-0.250 0.5009 0.01084 0.00413 -0.1100 0.6999 0.0441
0.000 0.5298 0.01041 0.00363 -0.1101 0.6849 0.0441
0.250 0.5585 0.01012 0.00326 -0.1102 0.6684 0.0444
0.500 0.5875 0.00977 0.00285 -0.1104 0.6484 0.0454
0.750 0.6162 0.00958 0.00255 -0.1106 0.6258 0.0474
1.000 0.6447 0.00954 0.00240 -0.1107 0.6020 0.0495
1.250 0.6729 0.00958 0.00232 -0.1108 0.5817 0.0524
1.500 0.7010 0.00965 0.00230 -0.1109 0.5651 0.0571
1.750 0.7299 0.00944 0.00237 -0.1113 0.5520 0.2116
2.250 0.7799 0.00809 0.00257 -0.1105 0.5318 1.0000
2.500 0.8079 0.00827 0.00267 -0.1105 0.5216 1.0000
2.750 0.8357 0.00848 0.00277 -0.1106 0.5110 1.0000
3.000 0.8636 0.00864 0.00287 -0.1106 0.5006 1.0000
3.250 0.8916 0.00879 0.00299 -0.1107 0.4923 1.0000
3.500 0.9194 0.00897 0.00313 -0.1108 0.4847 1.0000
3.750 0.9474 0.00911 0.00325 -0.1109 0.4762 1.0000
4.000 0.9750 0.00930 0.00339 -0.1109 0.4682 1.0000
4.250 1.0029 0.00942 0.00352 -0.1110 0.4585 1.0000
4.500 1.0304 0.00956 0.00366 -0.1110 0.4453 1.0000
4.750 1.0578 0.00972 0.00379 -0.1110 0.4316 1.0000
5.000 1.0851 0.00989 0.00393 -0.1110 0.4166 1.0000
5.250 1.1123 0.01007 0.00409 -0.1110 0.4027 1.0000
5.500 1.1389 0.01032 0.00428 -0.1109 0.3816 1.0000
5.750 1.1644 0.01073 0.00450 -0.1107 0.3388 1.0000
6.000 1.1869 0.01160 0.00494 -0.1103 0.2604 1.0000
6.250 1.2040 0.01331 0.00592 -0.1093 0.1448 1.0000
6.500 1.2253 0.01433 0.00662 -0.1086 0.0944 1.0000
6.750 1.2422 0.01590 0.00772 -0.1073 0.0214 1.0000
7.000 1.2657 0.01649 0.00836 -0.1067 0.0181 1.0000
7.250 1.2893 0.01704 0.00903 -0.1060 0.0163 1.0000
7.500 1.3119 0.01768 0.00979 -0.1052 0.0154 1.0000
7.750 1.3336 0.01837 0.01060 -0.1043 0.0146 1.0000
8.000 1.3539 0.01920 0.01152 -0.1032 0.0137 1.0000
8.250 1.3726 0.02013 0.01255 -0.1019 0.0131 1.0000
8.500 1.3893 0.02118 0.01371 -0.1003 0.0126 1.0000
8.750 1.4034 0.02240 0.01501 -0.0983 0.0121 1.0000
9.000 1.4142 0.02378 0.01649 -0.0959 0.0118 1.0000
9.250 1.4211 0.02532 0.01813 -0.0929 0.0115 1.0000
9.500 1.4242 0.02696 0.01987 -0.0894 0.0113 1.0000
9.750 1.4253 0.02862 0.02160 -0.0856 0.0112 1.0000
10.000 1.4260 0.03066 0.02371 -0.0821 0.0111 1.0000
10.250 1.4296 0.03324 0.02633 -0.0792 0.0108 1.0000
10.500 1.4376 0.03466 0.02790 -0.0771 0.0104 1.0000
10.750 1.4469 0.03618 0.02953 -0.0752 0.0102 1.0000
11.000 1.4566 0.03807 0.03153 -0.0733 0.0102 1.0000
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Polar data table (+)
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