GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 92 AIRFOIL (goe92-il) Reynolds number: 50,000 Max Cl/Cd: 36.95 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe92-il-50000-n5.txt Download as CSV file: xf-goe92-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 92 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2728 0.11347 0.10744 -0.0305 1.0000 0.0512
-8.000 -0.2774 0.11234 0.10645 -0.0312 1.0000 0.0514
-7.750 -0.2803 0.11104 0.10527 -0.0324 1.0000 0.0515
-7.500 -0.2655 0.10292 0.09719 -0.0274 1.0000 0.0535
-7.250 -0.2652 0.10015 0.09450 -0.0257 1.0000 0.0549
-7.000 -0.2685 0.09810 0.09255 -0.0244 1.0000 0.0562
-6.750 -0.2732 0.09628 0.09085 -0.0232 1.0000 0.0576
-6.500 -0.2782 0.09455 0.08920 -0.0222 1.0000 0.0591
-6.250 -0.2824 0.09280 0.08755 -0.0217 1.0000 0.0608
-6.000 -0.2852 0.09112 0.08595 -0.0221 1.0000 0.0629
-5.750 -0.2847 0.08992 0.08479 -0.0248 1.0000 0.0650
-5.500 -0.2567 0.08600 0.08083 -0.0337 0.9924 0.0669
-5.250 -0.2398 0.08088 0.07576 -0.0329 0.9859 0.0727
-5.000 -0.1902 0.07742 0.07203 -0.0481 0.9729 0.0809
-4.750 -0.1722 0.07217 0.06687 -0.0475 0.9658 0.0868
-4.500 -0.1325 0.06800 0.06255 -0.0563 0.9547 0.0971
-4.000 -0.0611 0.05984 0.05417 -0.0675 0.9313 0.1277
-3.750 -0.0232 0.05582 0.05005 -0.0727 0.9192 0.1579
-2.750 0.1669 0.04060 0.03313 -0.0925 0.8665 0.0899
-2.500 0.2062 0.03805 0.02997 -0.0940 0.8521 0.0789
-2.250 0.2373 0.03538 0.02699 -0.0946 0.8365 0.0740
-2.000 0.2713 0.03322 0.02425 -0.0948 0.8204 0.0687
-1.750 0.3008 0.03141 0.02212 -0.0948 0.8033 0.0720
-1.500 0.3315 0.02979 0.02008 -0.0945 0.7860 0.0736
-1.250 0.3623 0.02828 0.01811 -0.0940 0.7686 0.0728
-1.000 0.3910 0.02707 0.01653 -0.0933 0.7489 0.0737
-0.750 0.4195 0.02622 0.01525 -0.0924 0.7290 0.0794
-0.500 0.4489 0.02526 0.01391 -0.0915 0.7102 0.0803
-0.250 0.4780 0.02441 0.01274 -0.0907 0.6899 0.0809
0.000 0.5061 0.02367 0.01173 -0.0899 0.6706 0.0822
0.250 0.5336 0.02313 0.01090 -0.0890 0.6522 0.0839
0.500 0.5601 0.02282 0.01030 -0.0883 0.6332 0.0864
0.750 0.5867 0.02265 0.00986 -0.0876 0.6149 0.0910
1.000 0.6134 0.02253 0.00956 -0.0871 0.5976 0.1030
1.250 0.6403 0.02250 0.00936 -0.0867 0.5813 0.1173
1.500 0.6653 0.02165 0.00941 -0.0866 0.5662 0.4142
1.750 0.6927 0.02099 0.00931 -0.0858 0.5515 1.0000
2.000 0.7187 0.02141 0.00938 -0.0853 0.5379 1.0000
2.250 0.7447 0.02185 0.00955 -0.0849 0.5257 1.0000
2.500 0.7708 0.02230 0.00975 -0.0845 0.5148 1.0000
2.750 0.7968 0.02275 0.00999 -0.0842 0.5047 1.0000
3.000 0.8221 0.02325 0.01038 -0.0839 0.4944 1.0000
3.250 0.8479 0.02373 0.01072 -0.0837 0.4858 1.0000
3.500 0.8734 0.02425 0.01114 -0.0834 0.4774 1.0000
3.750 0.8989 0.02480 0.01165 -0.0832 0.4701 1.0000
4.000 0.9244 0.02536 0.01218 -0.0830 0.4632 1.0000
4.250 0.9499 0.02593 0.01271 -0.0828 0.4570 1.0000
4.500 0.9744 0.02656 0.01341 -0.0825 0.4502 1.0000
4.750 1.0006 0.02708 0.01387 -0.0823 0.4451 1.0000
5.000 1.0237 0.02786 0.01479 -0.0820 0.4385 1.0000
5.250 1.0487 0.02852 0.01551 -0.0818 0.4336 1.0000
5.500 1.0738 0.02919 0.01627 -0.0815 0.4290 1.0000
5.750 1.0959 0.03008 0.01735 -0.0811 0.4231 1.0000
6.000 1.1204 0.03077 0.01812 -0.0808 0.4183 1.0000
6.250 1.1438 0.03159 0.01912 -0.0805 0.4136 1.0000
6.500 1.1646 0.03258 0.02036 -0.0799 0.4078 1.0000
6.750 1.1895 0.03317 0.02102 -0.0796 0.4024 1.0000
7.000 1.2078 0.03415 0.02226 -0.0787 0.3946 1.0000
7.250 1.2331 0.03443 0.02264 -0.0781 0.3871 1.0000
7.500 1.2491 0.03535 0.02385 -0.0768 0.3774 1.0000
7.750 1.2695 0.03580 0.02444 -0.0757 0.3677 1.0000
8.000 1.2848 0.03559 0.02427 -0.0736 0.3487 1.0000
8.250 1.2993 0.03536 0.02401 -0.0714 0.3294 1.0000
8.500 1.3115 0.03576 0.02455 -0.0693 0.3140 1.0000
8.750 1.3217 0.03652 0.02562 -0.0672 0.3005 1.0000
9.000 1.3286 0.03725 0.02652 -0.0648 0.2844 1.0000
9.250 1.3290 0.03842 0.02795 -0.0621 0.2637 1.0000
9.500 1.3307 0.03974 0.02953 -0.0596 0.2466 1.0000
9.750 1.3308 0.04133 0.03132 -0.0573 0.2269 1.0000
10.000 1.3285 0.04333 0.03341 -0.0554 0.1964 1.0000
10.250 1.3209 0.04583 0.03566 -0.0536 0.1638 1.0000
10.750 1.2977 0.05335 0.04302 -0.0521 0.1269 1.0000
11.000 1.2832 0.05814 0.04786 -0.0524 0.1112 1.0000
11.500 1.2500 0.06942 0.05927 -0.0549 0.0560 1.0000
12.000 1.2120 0.08216 0.07203 -0.0585 0.0447 1.0000
12.250 1.1969 0.08809 0.07805 -0.0600 0.0420 1.0000
12.500 1.1834 0.09386 0.08392 -0.0616 0.0395 1.0000
12.750 1.1714 0.09948 0.08964 -0.0631 0.0376 1.0000
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Polar data table (+)
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