GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 528 AIRFOIL (goe528-il) Reynolds number: 50,000 Max Cl/Cd: 29.8 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe528-il-50000-n5.txt Download as CSV file: xf-goe528-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 528 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2386 0.12332 0.11691 -0.0360 1.0000 0.1048
-9.500 -0.2469 0.12225 0.11595 -0.0337 1.0000 0.1066
-9.250 -0.2578 0.12146 0.11527 -0.0315 1.0000 0.1089
-9.000 -0.2553 0.11980 0.11364 -0.0381 0.9909 0.1134
-8.750 -0.2576 0.11867 0.11256 -0.0462 0.9779 0.1145
-8.500 -0.2133 0.11043 0.10426 -0.0440 0.9768 0.1201
-8.250 -0.1977 0.10707 0.10089 -0.0476 0.9678 0.1248
-8.000 -0.1970 0.10534 0.09919 -0.0535 0.9550 0.1297
-7.750 -0.2031 0.10404 0.09793 -0.0616 0.9389 0.1310
-7.500 -0.1660 0.09740 0.09126 -0.0593 0.9375 0.1343
-7.250 -0.1460 0.09399 0.08782 -0.0615 0.9297 0.1413
-7.000 -0.1522 0.09265 0.08647 -0.0719 0.9124 0.1477
-6.750 -0.1252 0.08762 0.08147 -0.0691 0.9078 0.1518
-6.500 -0.1003 0.08379 0.07759 -0.0730 0.9017 0.1569
-6.000 -0.0802 0.06980 0.06311 -0.0942 0.8749 0.0846
-5.750 -0.0542 0.06573 0.05887 -0.0980 0.8683 0.0834
-5.500 -0.0414 0.06265 0.05569 -0.0991 0.8570 0.0830
-5.250 -0.0140 0.05867 0.05153 -0.1028 0.8507 0.0819
-5.000 -0.0004 0.05582 0.04854 -0.1034 0.8389 0.0806
-4.750 0.0304 0.05168 0.04408 -0.1074 0.8331 0.0791
-4.500 0.0453 0.04901 0.04115 -0.1077 0.8213 0.0787
-4.250 0.0759 0.04570 0.03739 -0.1105 0.8148 0.0800
-4.000 0.0956 0.04338 0.03468 -0.1107 0.8040 0.0808
-3.750 0.1267 0.04070 0.03153 -0.1122 0.7975 0.0808
-3.500 0.1481 0.03892 0.02937 -0.1118 0.7873 0.0810
-3.250 0.1833 0.03673 0.02667 -0.1133 0.7819 0.0819
-3.000 0.2031 0.03566 0.02515 -0.1121 0.7707 0.0837
-2.750 0.2379 0.03404 0.02332 -0.1133 0.7656 0.0866
-2.500 0.2564 0.03338 0.02250 -0.1118 0.7544 0.0883
-2.250 0.2920 0.03208 0.02090 -0.1126 0.7491 0.0906
-2.000 0.3117 0.03160 0.02024 -0.1112 0.7382 0.0927
-1.750 0.3471 0.03065 0.01896 -0.1119 0.7328 0.0976
-1.500 0.3663 0.03035 0.01862 -0.1104 0.7223 0.1021
-1.250 0.4012 0.02958 0.01768 -0.1110 0.7166 0.1089
-1.000 0.4226 0.02944 0.01739 -0.1098 0.7069 0.1151
-0.750 0.4548 0.02882 0.01670 -0.1102 0.7006 0.1295
-0.500 0.4769 0.02865 0.01658 -0.1093 0.6916 0.1489
-0.250 0.5067 0.02791 0.01620 -0.1095 0.6850 0.2126
0.000 0.5459 0.02557 0.01602 -0.1111 0.6786 1.0000
0.250 0.5686 0.02594 0.01602 -0.1101 0.6700 1.0000
0.500 0.6000 0.02599 0.01569 -0.1102 0.6643 1.0000
0.750 0.6166 0.02662 0.01613 -0.1085 0.6546 1.0000
1.000 0.6495 0.02659 0.01581 -0.1088 0.6494 1.0000
1.250 0.6638 0.02734 0.01643 -0.1069 0.6395 1.0000
1.500 0.6949 0.02740 0.01626 -0.1070 0.6340 1.0000
1.750 0.7108 0.02811 0.01686 -0.1054 0.6249 1.0000
2.000 0.7392 0.02827 0.01686 -0.1052 0.6188 1.0000
2.250 0.7586 0.02886 0.01734 -0.1040 0.6110 1.0000
2.500 0.7827 0.02923 0.01759 -0.1033 0.6038 1.0000
2.750 0.8108 0.02943 0.01766 -0.1030 0.5980 1.0000
3.000 0.8253 0.03026 0.01845 -0.1013 0.5892 1.0000
3.250 0.8588 0.03019 0.01825 -0.1017 0.5842 1.0000
3.500 0.8679 0.03130 0.01937 -0.0994 0.5748 1.0000
3.750 0.8980 0.03140 0.01938 -0.0993 0.5693 1.0000
4.000 0.9117 0.03231 0.02028 -0.0976 0.5609 1.0000
4.250 0.9361 0.03269 0.02062 -0.0969 0.5543 1.0000
4.500 0.9618 0.03302 0.02090 -0.0965 0.5482 1.0000
4.750 0.9729 0.03405 0.02195 -0.0944 0.5393 1.0000
5.000 1.0091 0.03386 0.02169 -0.0950 0.5346 1.0000
5.250 1.0084 0.03550 0.02341 -0.0918 0.5245 1.0000
5.500 1.0412 0.03544 0.02331 -0.0920 0.5191 1.0000
5.750 1.0433 0.03697 0.02490 -0.0891 0.5099 1.0000
6.000 1.0703 0.03718 0.02512 -0.0887 0.5035 1.0000
6.250 1.0792 0.03835 0.02634 -0.0866 0.4955 1.0000
6.500 1.0936 0.03919 0.02721 -0.0849 0.4880 1.0000
6.750 1.1296 0.03898 0.02700 -0.0855 0.4828 1.0000
7.000 1.1102 0.04154 0.02967 -0.0805 0.4723 1.0000
7.250 1.1538 0.04085 0.02898 -0.0817 0.4679 1.0000
7.500 1.1217 0.04444 0.03268 -0.0762 0.4563 1.0000
7.750 1.1624 0.04369 0.03196 -0.0768 0.4520 1.0000
8.000 1.1271 0.04809 0.03648 -0.0723 0.4400 1.0000
8.250 1.1664 0.04721 0.03563 -0.0724 0.4360 1.0000
8.500 1.1282 0.05252 0.04105 -0.0689 0.4233 1.0000
8.750 1.1663 0.05149 0.04006 -0.0686 0.4199 1.0000
9.250 1.1049 0.06287 0.05162 -0.0654 0.3952 1.0000
9.500 1.1227 0.06366 0.05248 -0.0645 0.3900 1.0000
9.750 1.1571 0.06258 0.05150 -0.0636 0.3875 1.0000
10.250 1.1403 0.07052 0.05959 -0.0625 0.3702 1.0000
10.750 1.1345 0.07770 0.06694 -0.0620 0.3551 1.0000
11.250 1.0666 0.09481 0.08418 -0.0650 0.3314 1.0000
11.500 1.0805 0.09635 0.08582 -0.0645 0.3273 1.0000
11.750 1.1035 0.09651 0.08611 -0.0636 0.3249 1.0000
12.000 1.0624 0.10663 0.09626 -0.0663 0.3137 1.0000
12.250 1.0775 0.10820 0.09796 -0.0660 0.3107 1.0000
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Polar data table (+)
Polar graphs
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