GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 650 AIRFOIL (goe650-il) Reynolds number: 50,000 Max Cl/Cd: 34.82 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe650-il-50000-n5.txt Download as CSV file: xf-goe650-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 650 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3637 0.11611 0.10812 -0.0470 1.0000 0.0902
-10.750 -0.3687 0.11250 0.10457 -0.0473 1.0000 0.0902
-10.500 -0.3781 0.10846 0.10060 -0.0479 1.0000 0.0905
-10.250 -0.3725 0.10697 0.09917 -0.0463 1.0000 0.0918
-10.000 -0.3715 0.10509 0.09734 -0.0451 1.0000 0.0934
-9.750 -0.3766 0.10253 0.09485 -0.0443 1.0000 0.0948
-9.500 -0.3857 0.09969 0.09209 -0.0436 1.0000 0.0962
-9.250 -0.3992 0.09643 0.08892 -0.0430 1.0000 0.0972
-9.000 -0.4168 0.09298 0.08557 -0.0423 1.0000 0.0982
-8.750 -0.4394 0.08930 0.08200 -0.0415 1.0000 0.0989
-8.500 -0.4677 0.08551 0.07834 -0.0403 1.0000 0.0993
-8.250 -0.5044 0.08114 0.07410 -0.0393 1.0000 0.0997
-8.000 -0.5528 0.07137 0.06440 -0.0440 1.0000 0.1006
-7.750 -0.5998 0.05661 0.04928 -0.0556 0.9996 0.1027
-7.500 -0.5708 0.05702 0.04975 -0.0558 0.9950 0.1063
-7.250 -0.5642 0.04643 0.03824 -0.0673 0.9878 0.1147
-7.000 -0.5354 0.04677 0.03871 -0.0674 0.9835 0.1194
-6.750 -0.5150 0.04227 0.03353 -0.0718 0.9782 0.1286
-6.500 -0.4869 0.04239 0.03376 -0.0722 0.9733 0.1351
-6.250 -0.4607 0.04034 0.03131 -0.0746 0.9686 0.1451
-6.000 -0.4351 0.03975 0.03059 -0.0753 0.9632 0.1544
-5.750 -0.4058 0.03929 0.03006 -0.0765 0.9586 0.1639
-5.500 -0.3805 0.03788 0.02823 -0.0779 0.9532 0.1750
-5.250 -0.3534 0.03783 0.02827 -0.0781 0.9477 0.1822
-5.000 -0.3208 0.03633 0.02630 -0.0805 0.9434 0.1916
-4.750 -0.2972 0.03602 0.02605 -0.0800 0.9367 0.1973
-4.500 -0.2660 0.03498 0.02463 -0.0816 0.9310 0.2059
-4.250 -0.2343 0.03446 0.02407 -0.0827 0.9255 0.2123
-4.000 -0.2087 0.03392 0.02338 -0.0828 0.9182 0.2197
-3.750 -0.1747 0.03329 0.02256 -0.0844 0.9129 0.2275
-3.500 -0.1485 0.03295 0.02216 -0.0844 0.9062 0.2345
-3.250 -0.1196 0.03249 0.02151 -0.0850 0.8997 0.2436
-3.000 -0.0848 0.03222 0.02123 -0.0864 0.8949 0.2527
-2.750 -0.0614 0.03194 0.02082 -0.0860 0.8873 0.2615
-2.500 -0.0308 0.03176 0.02060 -0.0867 0.8811 0.2724
-2.250 0.0056 0.03154 0.02037 -0.0882 0.8767 0.2844
-2.000 0.0242 0.03146 0.02020 -0.0869 0.8675 0.2956
-1.750 0.0574 0.03133 0.02005 -0.0879 0.8619 0.3102
-1.500 0.0830 0.03134 0.02010 -0.0876 0.8545 0.3236
-1.250 0.1118 0.03131 0.02006 -0.0878 0.8471 0.3397
-1.000 0.1498 0.03120 0.01994 -0.0894 0.8424 0.3599
-0.750 0.1685 0.03137 0.02013 -0.0881 0.8325 0.3758
-0.500 0.2042 0.03130 0.02005 -0.0893 0.8267 0.3982
-0.250 0.2270 0.03145 0.02022 -0.0885 0.8177 0.4168
0.000 0.2599 0.03142 0.02019 -0.0892 0.8108 0.4401
0.250 0.2872 0.03149 0.02031 -0.0891 0.8027 0.4607
0.500 0.3165 0.03148 0.02037 -0.0891 0.7943 0.4827
0.750 0.3479 0.03139 0.02034 -0.0894 0.7865 0.5068
1.000 0.3779 0.03123 0.02024 -0.0893 0.7765 0.5318
1.250 0.4061 0.03104 0.02015 -0.0889 0.7656 0.5569
1.500 0.4448 0.03044 0.01965 -0.0897 0.7574 0.5878
1.750 0.4691 0.03030 0.01962 -0.0887 0.7449 0.6162
2.000 0.5119 0.02949 0.01898 -0.0901 0.7385 0.6552
2.250 0.5321 0.02938 0.01909 -0.0884 0.7253 0.6949
2.500 0.5872 0.02805 0.01837 -0.0920 0.7183 0.8627
2.750 0.6102 0.02812 0.01831 -0.0910 0.7050 1.0000
3.000 0.6347 0.02828 0.01836 -0.0902 0.6917 1.0000
3.250 0.6723 0.02796 0.01792 -0.0910 0.6816 1.0000
3.500 0.7008 0.02789 0.01778 -0.0906 0.6686 1.0000
3.750 0.7226 0.02802 0.01787 -0.0891 0.6535 1.0000
4.000 0.7464 0.02807 0.01787 -0.0880 0.6386 1.0000
4.250 0.7717 0.02804 0.01781 -0.0869 0.6234 1.0000
4.500 0.7976 0.02798 0.01771 -0.0859 0.6077 1.0000
4.750 0.8244 0.02789 0.01757 -0.0850 0.5912 1.0000
5.000 0.8520 0.02778 0.01742 -0.0841 0.5739 1.0000
5.250 0.8804 0.02769 0.01726 -0.0834 0.5557 1.0000
5.500 0.9091 0.02765 0.01713 -0.0828 0.5366 1.0000
5.750 0.9371 0.02772 0.01710 -0.0821 0.5167 1.0000
6.000 0.9634 0.02792 0.01718 -0.0812 0.4965 1.0000
6.250 0.9858 0.02831 0.01745 -0.0799 0.4762 1.0000
6.500 1.0034 0.02888 0.01798 -0.0781 0.4560 1.0000
6.750 1.0208 0.02949 0.01852 -0.0763 0.4366 1.0000
7.000 1.0380 0.03012 0.01908 -0.0745 0.4183 1.0000
7.250 1.0550 0.03078 0.01969 -0.0727 0.4011 1.0000
7.500 1.0725 0.03148 0.02031 -0.0711 0.3852 1.0000
7.750 1.0905 0.03220 0.02094 -0.0695 0.3703 1.0000
8.000 1.1097 0.03292 0.02155 -0.0682 0.3565 1.0000
8.250 1.1254 0.03382 0.02248 -0.0665 0.3429 1.0000
8.500 1.1422 0.03473 0.02339 -0.0651 0.3304 1.0000
8.750 1.1623 0.03559 0.02420 -0.0640 0.3192 1.0000
9.000 1.1806 0.03652 0.02513 -0.0628 0.3080 1.0000
9.250 1.1965 0.03759 0.02628 -0.0614 0.2977 1.0000
9.500 1.2200 0.03844 0.02705 -0.0608 0.2884 1.0000
9.750 1.2307 0.03974 0.02852 -0.0589 0.2792 1.0000
10.000 1.2550 0.04060 0.02931 -0.0584 0.2709 1.0000
10.250 1.2625 0.04207 0.03101 -0.0563 0.2629 1.0000
10.500 1.2827 0.04311 0.03205 -0.0554 0.2557 1.0000
10.750 1.2939 0.04457 0.03366 -0.0538 0.2490 1.0000
11.000 1.3047 0.04601 0.03526 -0.0522 0.2424 1.0000
11.250 1.3280 0.04698 0.03618 -0.0517 0.2364 1.0000
11.500 1.3269 0.04907 0.03857 -0.0492 0.2308 1.0000
11.750 1.3364 0.05073 0.04039 -0.0477 0.2256 1.0000
12.000 1.3631 0.05160 0.04120 -0.0474 0.2205 1.0000
12.250 1.3521 0.05438 0.04433 -0.0447 0.2161 1.0000
12.500 1.3488 0.05683 0.04700 -0.0427 0.2114 1.0000
12.750 1.3637 0.05796 0.04815 -0.0416 0.2060 1.0000
13.000 1.3572 0.06070 0.05109 -0.0398 0.2016 1.0000
13.250 1.3371 0.06470 0.05538 -0.0380 0.1977 1.0000
13.500 1.3348 0.06714 0.05793 -0.0368 0.1925 1.0000
13.750 1.3394 0.06886 0.05968 -0.0358 0.1870 1.0000
14.000 1.2997 0.07574 0.06689 -0.0356 0.1843 1.0000
14.250 1.2417 0.08628 0.07775 -0.0377 0.1829 1.0000
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