GOE 510 AIRFOIL (goe510-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 510 AIRFOIL (goe510-il) Reynolds number: 200,000 Max Cl/Cd: 65.91 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe510-il-200000.txt Download as CSV file: xf-goe510-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 510 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1570 0.09719 0.09372 -0.0658 0.9616 0.0691
-8.000 -0.1794 0.09339 0.08994 -0.0774 0.9496 0.0720
-7.750 -0.1757 0.08805 0.08457 -0.0824 0.9432 0.0727
-7.500 -0.1390 0.08452 0.08104 -0.0826 0.9426 0.0737
-7.250 -0.1223 0.08219 0.07872 -0.0821 0.9357 0.0749
-7.000 -0.1057 0.07925 0.07576 -0.0845 0.9298 0.0769
-6.750 -0.0974 0.07592 0.07241 -0.0875 0.9214 0.0799
-6.500 -0.0969 0.06907 0.06537 -0.0978 0.9115 0.0843
-6.250 -0.0868 0.06693 0.06326 -0.0955 0.9021 0.0851
-6.000 -0.0596 0.06430 0.06063 -0.0969 0.8987 0.0867
-5.750 -0.0308 0.06122 0.05749 -0.1002 0.8962 0.0900
-5.500 -0.0336 0.05640 0.05239 -0.1029 0.8831 0.0969
-5.250 -0.0028 0.05388 0.04990 -0.1043 0.8813 0.0984
-5.000 0.0319 0.05162 0.04762 -0.1068 0.8797 0.1020
-4.750 0.0341 0.04818 0.04389 -0.1063 0.8672 0.1110
-4.500 0.0695 0.04591 0.04166 -0.1085 0.8651 0.1132
-4.250 0.0899 0.04422 0.03992 -0.1080 0.8573 0.1170
-4.000 0.1154 0.04098 0.03643 -0.1100 0.8507 0.1269
-3.750 0.1555 0.03895 0.03437 -0.1131 0.8477 0.1314
-3.500 0.1395 0.02820 0.02226 -0.1071 0.8348 0.0977
-3.250 0.1743 0.02375 0.01691 -0.1079 0.8309 0.0826
-3.000 0.1916 0.02223 0.01518 -0.1056 0.8202 0.0818
-2.750 0.2335 0.02050 0.01312 -0.1081 0.8147 0.0815
-2.500 0.2565 0.01974 0.01215 -0.1067 0.8037 0.0824
-2.250 0.2998 0.01886 0.01097 -0.1094 0.7967 0.0834
-2.000 0.3211 0.01790 0.00989 -0.1078 0.7844 0.0841
-1.750 0.3530 0.01698 0.00889 -0.1084 0.7743 0.0853
-1.500 0.3864 0.01630 0.00814 -0.1092 0.7637 0.0870
-1.250 0.4091 0.01590 0.00773 -0.1079 0.7504 0.0890
-1.000 0.4353 0.01555 0.00732 -0.1073 0.7377 0.0920
-0.750 0.4635 0.01521 0.00689 -0.1070 0.7251 0.0947
-0.500 0.4903 0.01483 0.00643 -0.1065 0.7119 0.0972
-0.250 0.5105 0.01455 0.00616 -0.1046 0.6970 0.1004
0.000 0.5319 0.01439 0.00596 -0.1030 0.6818 0.1056
0.250 0.5531 0.01425 0.00577 -0.1014 0.6665 0.1124
0.500 0.5740 0.01415 0.00563 -0.0998 0.6510 0.1237
0.750 0.5930 0.01394 0.00561 -0.0978 0.6354 0.1705
1.000 0.6137 0.01403 0.00581 -0.0961 0.6198 0.2583
1.250 0.6349 0.01424 0.00593 -0.0946 0.6045 0.2906
1.500 0.6560 0.01440 0.00600 -0.0931 0.5902 0.3129
1.750 0.6745 0.01450 0.00606 -0.0911 0.5760 0.3310
2.000 0.6920 0.01457 0.00611 -0.0889 0.5626 0.3471
2.250 0.7106 0.01463 0.00614 -0.0870 0.5508 0.3637
2.500 0.7299 0.01466 0.00613 -0.0853 0.5403 0.3851
3.000 0.7566 0.01413 0.00615 -0.0794 0.5211 0.5825
3.250 0.9860 0.01509 0.00757 -0.1217 0.4968 1.0000
3.500 1.0056 0.01536 0.00767 -0.1201 0.4894 1.0000
3.750 1.0207 0.01556 0.00786 -0.1177 0.4819 1.0000
4.000 1.0389 0.01580 0.00800 -0.1158 0.4750 1.0000
4.250 1.0568 0.01607 0.00820 -0.1139 0.4682 1.0000
4.500 1.0726 0.01629 0.00840 -0.1116 0.4615 1.0000
4.750 1.0961 0.01663 0.00859 -0.1109 0.4554 1.0000
5.000 1.1094 0.01686 0.00886 -0.1081 0.4495 1.0000
5.250 1.1260 0.01711 0.00908 -0.1059 0.4435 1.0000
5.500 1.1505 0.01748 0.00932 -0.1055 0.4376 1.0000
5.750 1.1614 0.01771 0.00962 -0.1022 0.4319 1.0000
6.000 1.1777 0.01799 0.00987 -0.1000 0.4261 1.0000
6.250 1.2048 0.01840 0.01016 -0.1002 0.4207 1.0000
6.500 1.2135 0.01865 0.01051 -0.0965 0.4155 1.0000
6.750 1.2285 0.01893 0.01079 -0.0941 0.4100 1.0000
7.000 1.2536 0.01933 0.01108 -0.0938 0.4044 1.0000
7.250 1.2629 0.01962 0.01146 -0.0903 0.3993 1.0000
7.500 1.2747 0.01990 0.01179 -0.0873 0.3939 1.0000
7.750 1.2947 0.02024 0.01207 -0.0860 0.3889 1.0000
8.000 1.3095 0.02061 0.01247 -0.0836 0.3837 1.0000
8.250 1.3150 0.02086 0.01279 -0.0794 0.3783 1.0000
8.500 1.3280 0.02110 0.01301 -0.0767 0.3727 1.0000
8.750 1.3388 0.02142 0.01333 -0.0737 0.3666 1.0000
9.000 1.3414 0.02165 0.01364 -0.0691 0.3604 1.0000
9.250 1.3537 0.02189 0.01379 -0.0664 0.3538 1.0000
9.500 1.3545 0.02220 0.01421 -0.0617 0.3470 1.0000
9.750 1.3601 0.02248 0.01452 -0.0580 0.3403 1.0000
10.000 1.3699 0.02286 0.01489 -0.0552 0.3338 1.0000
10.250 1.3732 0.02328 0.01541 -0.0513 0.3268 1.0000
10.500 1.3833 0.02369 0.01573 -0.0487 0.3202 1.0000
10.750 1.3876 0.02426 0.01645 -0.0453 0.3135 1.0000
11.000 1.3945 0.02480 0.01701 -0.0425 0.3067 1.0000
11.250 1.4013 0.02544 0.01772 -0.0397 0.2998 1.0000
11.500 1.4069 0.02615 0.01848 -0.0370 0.2924 1.0000
11.750 1.4129 0.02693 0.01928 -0.0344 0.2851 1.0000
12.000 1.4188 0.02779 0.02022 -0.0319 0.2775 1.0000
12.250 1.4240 0.02875 0.02120 -0.0295 0.2701 1.0000
12.500 1.4276 0.02984 0.02236 -0.0272 0.2611 1.0000
12.750 1.4301 0.03109 0.02364 -0.0249 0.2517 1.0000
13.000 1.4310 0.03253 0.02507 -0.0226 0.2425 1.0000
13.250 1.4331 0.03403 0.02665 -0.0206 0.2317 1.0000
13.500 1.4329 0.03580 0.02844 -0.0187 0.2205 1.0000
13.750 1.4316 0.03775 0.03039 -0.0169 0.2112 1.0000
14.000 1.4272 0.04010 0.03273 -0.0152 0.1974 1.0000
14.250 1.4240 0.04250 0.03515 -0.0138 0.1840 1.0000
14.500 1.4174 0.04535 0.03798 -0.0125 0.1697 1.0000
14.750 1.4117 0.04825 0.04089 -0.0114 0.1568 1.0000
15.000 1.3983 0.05206 0.04464 -0.0105 0.1407 1.0000
15.250 1.3824 0.05634 0.04887 -0.0098 0.1242 1.0000
15.500 1.3690 0.06051 0.05304 -0.0094 0.1126 1.0000
15.750 1.3542 0.06499 0.05752 -0.0093 0.1013 1.0000
16.000 1.3376 0.06986 0.06240 -0.0094 0.0894 1.0000
16.250 1.3167 0.07545 0.06798 -0.0099 0.0742 1.0000
16.500 1.2939 0.08145 0.07396 -0.0107 0.0520 1.0000
16.750 1.2692 0.08792 0.08040 -0.0118 0.0422 1.0000
17.000 1.2518 0.09350 0.08603 -0.0128 0.0393 1.0000
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Polar data table (+)
Polar graphs
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