GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 264 AIRFOIL (goe264-il) Reynolds number: 50,000 Max Cl/Cd: 41.85 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe264-il-50000-n5.txt Download as CSV file: xf-goe264-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 264 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2960 0.10013 0.09373 -0.0246 1.0000 0.0774
-7.000 -0.2952 0.09842 0.09213 -0.0260 1.0000 0.0798
-6.750 -0.2938 0.09743 0.09124 -0.0294 1.0000 0.0812
-6.500 -0.2882 0.09635 0.09020 -0.0339 1.0000 0.0818
-6.250 -0.2861 0.09121 0.08514 -0.0296 1.0000 0.0835
-6.000 -0.2826 0.08804 0.08202 -0.0271 1.0000 0.0877
-5.750 -0.2764 0.08604 0.08006 -0.0289 1.0000 0.0928
-5.500 -0.2553 0.08582 0.07975 -0.0391 1.0000 0.0958
-5.250 -0.2559 0.08108 0.07514 -0.0351 1.0000 0.0971
-5.000 -0.2523 0.07777 0.07189 -0.0328 1.0000 0.0996
-4.750 -0.2427 0.07510 0.06923 -0.0333 1.0000 0.1035
-4.250 -0.2030 0.06897 0.06304 -0.0402 0.9967 0.1164
-3.750 -0.1120 0.06051 0.05419 -0.0568 0.9798 0.1325
-3.500 -0.0664 0.05681 0.05030 -0.0643 0.9708 0.1482
-3.250 -0.0182 0.05307 0.04634 -0.0720 0.9621 0.1593
-2.750 0.0984 0.04448 0.03679 -0.0892 0.9436 0.1036
-2.500 0.1507 0.04146 0.03340 -0.0957 0.9354 0.1044
-2.250 0.2067 0.03819 0.02943 -0.1022 0.9251 0.0952
-2.000 0.2493 0.03576 0.02672 -0.1060 0.9137 0.0938
-1.750 0.2927 0.03359 0.02419 -0.1095 0.9020 0.0931
-1.500 0.3355 0.03162 0.02183 -0.1125 0.8900 0.0932
-1.250 0.3747 0.03012 0.02003 -0.1148 0.8767 0.0983
-1.000 0.4105 0.02896 0.01867 -0.1163 0.8619 0.1032
-0.750 0.4465 0.02763 0.01701 -0.1174 0.8467 0.1044
-0.500 0.4810 0.02648 0.01552 -0.1181 0.8309 0.1062
-0.250 0.5139 0.02549 0.01419 -0.1184 0.8144 0.1087
0.000 0.5449 0.02470 0.01314 -0.1182 0.7975 0.1125
0.250 0.5746 0.02421 0.01247 -0.1179 0.7800 0.1222
0.500 0.6035 0.02366 0.01177 -0.1173 0.7627 0.1304
0.750 0.6305 0.02320 0.01112 -0.1165 0.7436 0.1378
1.000 0.6575 0.02278 0.01061 -0.1157 0.7254 0.1474
1.250 0.6846 0.02247 0.01020 -0.1150 0.7078 0.1673
1.500 0.7120 0.02215 0.00988 -0.1145 0.6910 0.1963
1.750 0.7398 0.02183 0.00961 -0.1141 0.6748 0.2402
2.000 0.7600 0.02018 0.00940 -0.1124 0.6594 1.0000
2.250 0.7872 0.02050 0.00931 -0.1117 0.6434 1.0000
2.500 0.8142 0.02084 0.00939 -0.1112 0.6280 1.0000
2.750 0.8411 0.02122 0.00959 -0.1108 0.6134 1.0000
3.000 0.8680 0.02163 0.00983 -0.1104 0.5994 1.0000
3.250 0.8946 0.02205 0.01015 -0.1100 0.5858 1.0000
3.500 0.9208 0.02253 0.01059 -0.1097 0.5723 1.0000
3.750 0.9469 0.02303 0.01107 -0.1094 0.5595 1.0000
4.000 0.9729 0.02354 0.01157 -0.1091 0.5475 1.0000
4.250 0.9990 0.02405 0.01212 -0.1088 0.5365 1.0000
4.500 1.0254 0.02455 0.01262 -0.1085 0.5266 1.0000
4.750 1.0506 0.02516 0.01333 -0.1082 0.5158 1.0000
5.000 1.0763 0.02576 0.01401 -0.1079 0.5064 1.0000
5.250 1.1023 0.02634 0.01469 -0.1076 0.4980 1.0000
5.500 1.1270 0.02706 0.01559 -0.1073 0.4891 1.0000
5.750 1.1534 0.02765 0.01626 -0.1070 0.4822 1.0000
6.000 1.1771 0.02849 0.01739 -0.1066 0.4735 1.0000
6.250 1.2034 0.02912 0.01815 -0.1063 0.4674 1.0000
6.500 1.2262 0.03013 0.01947 -0.1059 0.4599 1.0000
6.750 1.2517 0.03090 0.02045 -0.1056 0.4541 1.0000
7.000 1.2742 0.03196 0.02184 -0.1051 0.4474 1.0000
7.250 1.2980 0.03287 0.02311 -0.1046 0.4411 1.0000
7.500 1.3193 0.03360 0.02417 -0.1035 0.4303 1.0000
7.750 1.3356 0.03266 0.02321 -0.1004 0.3979 1.0000
8.000 1.3431 0.03223 0.02276 -0.0965 0.3558 1.0000
8.250 1.3498 0.03262 0.02325 -0.0932 0.3136 1.0000
8.500 1.3505 0.03376 0.02430 -0.0896 0.2365 1.0000
8.750 1.3312 0.03742 0.02668 -0.0850 0.1126 1.0000
9.000 1.3197 0.04091 0.02998 -0.0814 0.0798 1.0000
9.250 1.3095 0.04419 0.03323 -0.0784 0.0684 1.0000
9.500 1.2995 0.04771 0.03682 -0.0762 0.0629 1.0000
9.750 1.2884 0.05162 0.04089 -0.0748 0.0594 1.0000
10.000 1.2797 0.05559 0.04507 -0.0741 0.0561 1.0000
10.250 1.2704 0.05992 0.04958 -0.0739 0.0532 1.0000
10.500 1.2607 0.06450 0.05430 -0.0741 0.0509 1.0000
10.750 1.2502 0.06929 0.05920 -0.0745 0.0488 1.0000
11.000 1.2426 0.07367 0.06366 -0.0746 0.0470 1.0000
11.250 1.2406 0.07726 0.06745 -0.0742 0.0451 1.0000
11.500 1.2405 0.08044 0.07079 -0.0734 0.0434 1.0000
11.750 1.2426 0.08327 0.07375 -0.0723 0.0414 1.0000
12.000 1.2459 0.08587 0.07641 -0.0710 0.0393 1.0000
12.250 1.2546 0.08752 0.07802 -0.0685 0.0368 1.0000
12.500 1.2655 0.08956 0.08038 -0.0667 0.0350 1.0000
12.750 1.2818 0.09113 0.08225 -0.0641 0.0336 1.0000
13.000 1.2928 0.09375 0.08516 -0.0624 0.0327 1.0000
13.250 1.2961 0.09746 0.08914 -0.0621 0.0319 1.0000
13.500 1.2945 0.10178 0.09371 -0.0626 0.0313 1.0000
13.750 1.2904 0.10648 0.09872 -0.0636 0.0306 1.0000
14.000 1.2834 0.11168 0.10414 -0.0653 0.0302 1.0000
14.250 1.2745 0.11733 0.11001 -0.0676 0.0299 1.0000
14.500 1.2640 0.12349 0.11639 -0.0706 0.0297 1.0000
14.750 1.2509 0.13054 0.12368 -0.0746 0.0297 1.0000
15.000 1.2345 0.13890 0.13227 -0.0799 0.0301 1.0000
15.250 1.2112 0.15013 0.14370 -0.0878 0.0312 1.0000
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Polar data table (+)
Polar graphs
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