GOE 386 AIRFOIL (goe386-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 386 AIRFOIL (goe386-il) Reynolds number: 100,000 Max Cl/Cd: 33.24 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe386-il-100000.txt Download as CSV file: xf-goe386-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 386 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0225 0.10521 0.10016 -0.0941 0.9218 0.1880
-9.250 0.0082 0.09982 0.09474 -0.0956 0.9118 0.1895
-9.000 0.0382 0.09637 0.09125 -0.0951 0.8967 0.1914
-8.750 0.0570 0.09366 0.08850 -0.0950 0.8815 0.1945
-8.500 0.0635 0.09119 0.08597 -0.0955 0.8678 0.2000
-8.250 0.0214 0.08820 0.08298 -0.1002 0.8505 0.2058
-8.000 0.0537 0.08549 0.08022 -0.0975 0.8377 0.2078
-7.750 -0.1645 0.05156 0.04531 -0.1207 0.8230 0.1344
-7.500 -0.1215 0.05296 0.04699 -0.1196 0.8130 0.1375
-7.250 -0.1593 0.04433 0.03746 -0.1191 0.8047 0.1333
-7.000 -0.1594 0.04148 0.03421 -0.1172 0.7939 0.1337
-6.750 -0.1473 0.03849 0.03067 -0.1163 0.7880 0.1345
-6.500 -0.1344 0.03689 0.02884 -0.1149 0.7795 0.1355
-6.250 -0.1132 0.03570 0.02756 -0.1142 0.7724 0.1368
-6.000 -0.0858 0.03458 0.02633 -0.1142 0.7675 0.1389
-5.750 -0.0671 0.03380 0.02540 -0.1131 0.7604 0.1412
-5.500 -0.0485 0.03281 0.02415 -0.1120 0.7532 0.1437
-5.250 -0.0235 0.03152 0.02243 -0.1116 0.7484 0.1462
-5.000 0.0075 0.03053 0.02140 -0.1120 0.7448 0.1489
-4.750 0.0210 0.03065 0.02158 -0.1102 0.7372 0.1516
-4.500 0.0443 0.03025 0.02106 -0.1095 0.7319 0.1556
-4.250 0.0729 0.02948 0.02005 -0.1095 0.7277 0.1600
-4.000 0.1052 0.02883 0.01943 -0.1099 0.7243 0.1646
-3.750 0.1169 0.02919 0.01981 -0.1078 0.7171 0.1689
-3.500 0.1387 0.02904 0.01960 -0.1070 0.7119 0.1750
-3.250 0.1689 0.02856 0.01916 -0.1070 0.7074 0.1833
-3.000 0.2044 0.02774 0.01828 -0.1077 0.7035 0.1945
-2.750 0.2142 0.02814 0.01872 -0.1051 0.6944 0.2058
-2.500 0.2429 0.02749 0.01819 -0.1048 0.6881 0.2272
-2.250 0.2783 0.02675 0.01740 -0.1052 0.6834 0.2622
-2.000 0.2906 0.02725 0.01805 -0.1031 0.6759 0.2823
-1.750 0.3120 0.02740 0.01828 -0.1021 0.6699 0.3026
-1.500 0.3426 0.02715 0.01805 -0.1021 0.6654 0.3226
-1.250 0.3776 0.02682 0.01768 -0.1028 0.6616 0.3430
-1.000 0.3841 0.02773 0.01873 -0.1000 0.6538 0.3553
-0.750 0.4083 0.02783 0.01884 -0.0993 0.6478 0.3736
-0.500 0.4417 0.02741 0.01846 -0.0997 0.6433 0.3950
-0.250 0.4747 0.02713 0.01821 -0.1001 0.6391 0.4199
0.000 0.4775 0.02809 0.01945 -0.0968 0.6302 0.4396
0.250 0.5055 0.02775 0.01932 -0.0964 0.6246 0.4826
0.500 0.5398 0.02689 0.01885 -0.0965 0.6204 0.5748
0.750 0.5454 0.02714 0.01986 -0.0921 0.6130 0.7335
1.000 0.6348 0.02694 0.01991 -0.1010 0.6046 0.9774
1.250 0.7158 0.02647 0.01908 -0.1102 0.5989 1.0000
1.500 0.7165 0.02728 0.01984 -0.1061 0.5912 1.0000
1.750 0.7272 0.02768 0.02015 -0.1034 0.5833 1.0000
2.000 0.7623 0.02738 0.01961 -0.1040 0.5778 1.0000
2.250 0.7672 0.02811 0.02031 -0.1004 0.5694 1.0000
2.500 0.7826 0.02840 0.02051 -0.0983 0.5611 1.0000
2.750 0.8223 0.02801 0.01989 -0.0996 0.5558 1.0000
3.000 0.8207 0.02902 0.02093 -0.0951 0.5460 1.0000
3.250 0.8459 0.02906 0.02085 -0.0943 0.5386 1.0000
3.500 0.8898 0.02861 0.02015 -0.0963 0.5337 1.0000
3.750 0.8805 0.02985 0.02151 -0.0908 0.5224 1.0000
4.000 0.9161 0.02953 0.02101 -0.0915 0.5162 1.0000
4.250 0.9381 0.02985 0.02124 -0.0905 0.5091 1.0000
4.500 0.9448 0.03060 0.02202 -0.0874 0.4999 1.0000
4.750 0.9844 0.03024 0.02146 -0.0887 0.4950 1.0000
5.000 0.9878 0.03134 0.02261 -0.0853 0.4868 1.0000
5.250 1.0031 0.03187 0.02311 -0.0835 0.4796 1.0000
5.500 1.0448 0.03143 0.02248 -0.0852 0.4752 1.0000
5.750 1.0421 0.03280 0.02394 -0.0811 0.4676 1.0000
6.000 1.0532 0.03353 0.02468 -0.0788 0.4610 1.0000
6.250 1.0934 0.03317 0.02416 -0.0803 0.4569 1.0000
6.500 1.1120 0.03387 0.02483 -0.0792 0.4521 1.0000
6.750 1.0755 0.03663 0.02780 -0.0712 0.4444 1.0000
7.000 1.1079 0.03660 0.02769 -0.0717 0.4404 1.0000
7.250 1.1632 0.03579 0.02670 -0.0752 0.4373 1.0000
7.500 1.0152 0.04566 0.03707 -0.0584 0.4252 1.0000
7.750 1.0597 0.04445 0.03577 -0.0593 0.4228 1.0000
8.000 1.1188 0.04255 0.03374 -0.0616 0.4210 1.0000
8.250 1.1829 0.04084 0.03186 -0.0649 0.4192 1.0000
10.250 0.5788 0.14086 0.13333 -0.0651 0.4090 1.0000
10.500 0.6005 0.14277 0.13523 -0.0652 0.4041 1.0000
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Polar data table (+)
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