GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 392 AIRFOIL (goe392-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.59 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe392-il-1000000-n5.txt Download as CSV file: xf-goe392-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 392 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2901 0.12618 0.12454 -0.0435 0.9968 0.0023
-10.750 -0.2669 0.11811 0.11646 -0.0496 0.9938 0.0023
-10.500 -0.2557 0.11462 0.11298 -0.0524 0.9920 0.0024
-10.250 -0.2449 0.11080 0.10916 -0.0552 0.9902 0.0024
-9.750 -0.2249 0.10354 0.10190 -0.0604 0.9861 0.0026
-8.250 -0.1569 0.08055 0.07892 -0.0798 0.9491 0.0032
-7.750 -0.0813 0.06547 0.06367 -0.1068 0.9102 0.0021
-7.500 -0.0672 0.06152 0.05945 -0.1128 0.8532 0.0024
-7.250 -0.0629 0.05995 0.05774 -0.1134 0.8243 0.0030
-6.750 -0.0530 0.05230 0.04994 -0.1202 0.7930 0.0030
-6.500 -0.0437 0.04732 0.04488 -0.1248 0.7815 0.0028
-6.250 -0.0313 0.04191 0.03935 -0.1292 0.7717 0.0028
-6.000 -0.0170 0.03748 0.03474 -0.1316 0.7627 0.0031
-5.750 -0.0007 0.03274 0.02976 -0.1329 0.7542 0.0036
-5.500 0.0152 0.02899 0.02576 -0.1333 0.7464 0.0034
-5.250 0.0329 0.02542 0.02188 -0.1331 0.7385 0.0032
-5.000 0.0519 0.02186 0.01796 -0.1324 0.7315 0.0030
-4.750 0.0715 0.01799 0.01363 -0.1310 0.7237 0.0028
-4.500 0.0887 0.01215 0.00699 -0.1282 0.7173 0.0026
-4.250 0.1124 0.01092 0.00550 -0.1274 0.7094 0.0027
-4.000 0.1367 0.01009 0.00447 -0.1267 0.7020 0.0030
-3.750 0.1613 0.00951 0.00372 -0.1261 0.6934 0.0034
-3.500 0.1867 0.00908 0.00315 -0.1257 0.6849 0.0038
-3.250 0.2117 0.00867 0.00260 -0.1251 0.6751 0.0042
-3.000 0.2372 0.00856 0.00242 -0.1248 0.6622 0.0053
-2.750 0.2624 0.00836 0.00209 -0.1243 0.6469 0.0061
-2.500 0.2877 0.00814 0.00172 -0.1238 0.6322 0.0079
-2.250 0.3136 0.00805 0.00157 -0.1235 0.6203 0.0108
-2.000 0.3397 0.00797 0.00145 -0.1232 0.6090 0.0189
-1.750 0.3660 0.00794 0.00134 -0.1230 0.5980 0.0231
-1.500 0.3922 0.00790 0.00124 -0.1228 0.5880 0.0291
-1.250 0.4183 0.00789 0.00116 -0.1226 0.5780 0.0356
-1.000 0.4445 0.00785 0.00109 -0.1224 0.5677 0.0484
-0.750 0.4687 0.00743 0.00102 -0.1220 0.5591 0.1983
-0.250 0.5197 0.00720 0.00105 -0.1215 0.5428 0.3317
0.000 0.5460 0.00724 0.00107 -0.1213 0.5355 0.3524
0.250 0.5724 0.00724 0.00110 -0.1212 0.5281 0.3768
0.500 0.5985 0.00728 0.00113 -0.1210 0.5205 0.3917
0.750 0.6251 0.00732 0.00116 -0.1208 0.5131 0.4014
1.000 0.6510 0.00735 0.00121 -0.1206 0.5063 0.4213
1.250 0.6772 0.00733 0.00126 -0.1205 0.5000 0.4467
1.500 0.7029 0.00733 0.00132 -0.1202 0.4936 0.4788
1.750 0.7258 0.00702 0.00145 -0.1195 0.4879 0.6556
2.000 0.7497 0.00693 0.00155 -0.1189 0.4812 0.7300
2.250 0.7688 0.00660 0.00166 -0.1170 0.4753 0.8955
2.500 0.8224 0.00682 0.00185 -0.1233 0.4418 1.0000
2.750 0.8436 0.00718 0.00202 -0.1222 0.4007 1.0000
3.000 0.8621 0.00775 0.00228 -0.1206 0.3430 1.0000
3.250 0.8742 0.00876 0.00276 -0.1178 0.2429 1.0000
3.500 0.8738 0.01072 0.00384 -0.1128 0.0157 1.0000
3.750 0.8976 0.01095 0.00408 -0.1122 0.0105 1.0000
4.000 0.9210 0.01120 0.00436 -0.1115 0.0075 1.0000
4.250 0.9439 0.01147 0.00466 -0.1107 0.0061 1.0000
4.500 0.9651 0.01187 0.00512 -0.1095 0.0049 1.0000
4.750 0.9879 0.01213 0.00538 -0.1087 0.0038 1.0000
5.000 1.0091 0.01250 0.00578 -0.1076 0.0034 1.0000
5.250 1.0273 0.01307 0.00642 -0.1059 0.0029 1.0000
5.500 1.0449 0.01365 0.00709 -0.1040 0.0028 1.0000
5.750 1.0599 0.01435 0.00790 -0.1016 0.0025 1.0000
6.000 1.0705 0.01520 0.00886 -0.0984 0.0024 1.0000
6.250 1.0773 0.01606 0.00981 -0.0945 0.0023 1.0000
6.500 1.0824 0.01701 0.01084 -0.0904 0.0022 1.0000
6.750 1.1079 0.01697 0.01078 -0.0905 0.0018 1.0000
7.000 1.1112 0.01807 0.01196 -0.0863 0.0016 1.0000
7.250 1.1133 0.01936 0.01336 -0.0821 0.0016 1.0000
7.500 1.1181 0.02075 0.01484 -0.0784 0.0015 1.0000
7.750 1.1307 0.02312 0.01728 -0.0756 0.0013 1.0000
8.000 1.1961 0.02710 0.02135 -0.0815 0.0011 1.0000
8.250 1.2414 0.03086 0.02532 -0.0840 0.0011 1.0000
8.500 1.2674 0.03411 0.02880 -0.0832 0.0011 1.0000
8.750 1.2856 0.03699 0.03190 -0.0814 0.0012 1.0000
9.000 1.2985 0.03975 0.03486 -0.0791 0.0013 1.0000
9.250 1.3065 0.04261 0.03794 -0.0762 0.0014 1.0000
9.500 1.3092 0.04543 0.04096 -0.0730 0.0015 1.0000
9.750 1.2999 0.04943 0.04518 -0.0689 0.0016 1.0000
10.000 1.2976 0.05233 0.04826 -0.0652 0.0016 1.0000
10.250 1.2905 0.05471 0.05081 -0.0608 0.0016 1.0000
10.500 1.2797 0.05715 0.05341 -0.0561 0.0016 1.0000
10.750 1.2674 0.05966 0.05608 -0.0518 0.0016 1.0000
11.000 1.2531 0.06246 0.05903 -0.0480 0.0016 1.0000
11.250 1.2383 0.06536 0.06208 -0.0449 0.0016 1.0000
11.500 1.2223 0.06857 0.06544 -0.0423 0.0016 1.0000
11.750 1.2065 0.07194 0.06895 -0.0405 0.0016 1.0000
12.000 1.1897 0.07569 0.07284 -0.0393 0.0016 1.0000
12.250 1.1709 0.08004 0.07733 -0.0387 0.0016 1.0000
12.500 1.1532 0.08448 0.08190 -0.0388 0.0016 1.0000
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Polar data table (+)
Polar graphs
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