GOE 360 AIRFOIL (goe360-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 360 AIRFOIL (goe360-il) Reynolds number: 100,000 Max Cl/Cd: 51.39 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe360-il-100000.txt Download as CSV file: xf-goe360-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 360 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2893 0.09916 0.09506 -0.0232 1.0000 0.0516
-7.250 -0.3081 0.09883 0.09484 -0.0195 1.0000 0.0518
-7.000 -0.3239 0.09819 0.09431 -0.0169 1.0000 0.0522
-6.750 -0.3015 0.09424 0.09034 -0.0231 0.9939 0.0544
-6.500 -0.2557 0.09016 0.08615 -0.0403 0.9815 0.0587
-6.250 -0.2124 0.08503 0.08089 -0.0550 0.9711 0.0600
-6.000 -0.1945 0.07965 0.07556 -0.0536 0.9638 0.0616
-5.750 -0.1592 0.07501 0.07087 -0.0595 0.9572 0.0647
-5.500 -0.1209 0.07100 0.06674 -0.0681 0.9463 0.0691
-5.250 -0.0699 0.06634 0.06186 -0.0810 0.9376 0.0734
-5.000 -0.0422 0.06218 0.05771 -0.0831 0.9296 0.0772
-4.750 0.0191 0.06156 0.05644 -0.0961 0.9172 0.0859
-4.500 0.0399 0.05482 0.04994 -0.0968 0.9115 0.0881
-4.250 0.0634 0.05195 0.04705 -0.0979 0.8995 0.0927
-4.000 0.1010 0.04960 0.04435 -0.1028 0.8877 0.1018
-3.750 0.1264 0.04646 0.04124 -0.1035 0.8798 0.1091
-3.500 0.1521 0.04424 0.03880 -0.1049 0.8666 0.1188
-3.250 0.1794 0.04263 0.03692 -0.1062 0.8540 0.1318
-3.000 0.2047 0.04098 0.03507 -0.1066 0.8424 0.1465
-2.750 0.2294 0.03850 0.03250 -0.1068 0.8338 0.1625
-2.500 0.2490 0.03643 0.03041 -0.1062 0.8210 0.1798
-1.500 0.3018 0.01272 0.00722 -0.0925 0.7538 0.3772
-1.250 0.3199 0.01106 0.00559 -0.0906 0.7439 0.4310
-1.000 0.3417 0.00984 0.00435 -0.0894 0.7328 0.4698
-0.750 0.3768 0.00890 0.00307 -0.0911 0.7232 0.4744
-0.500 0.4307 0.00879 0.00212 -0.0962 0.7129 0.3626
-0.250 0.5069 0.02427 0.01594 -0.1043 0.7217 0.1899
0.000 0.5393 0.02330 0.01456 -0.1034 0.7115 0.1564
0.250 0.5686 0.02259 0.01354 -0.1024 0.6987 0.1352
0.500 0.5970 0.02202 0.01273 -0.1016 0.6862 0.1227
0.750 0.6255 0.02175 0.01216 -0.1006 0.6741 0.1140
1.000 0.6531 0.02106 0.01135 -0.1000 0.6628 0.1104
1.250 0.6802 0.02063 0.01080 -0.0992 0.6508 0.1078
1.500 0.7062 0.02037 0.01050 -0.0985 0.6378 0.1088
1.750 0.7317 0.02020 0.01028 -0.0977 0.6254 0.1123
2.000 0.7578 0.02008 0.01005 -0.0969 0.6142 0.1139
2.250 0.7849 0.01997 0.00979 -0.0964 0.6035 0.1166
2.500 0.8106 0.02004 0.00981 -0.0959 0.5911 0.1228
2.750 0.8370 0.02014 0.00986 -0.0955 0.5799 0.1368
3.000 0.8650 0.01853 0.00983 -0.0951 0.5712 1.0000
3.250 0.8900 0.01895 0.01005 -0.0945 0.5597 1.0000
3.500 0.9157 0.01934 0.01026 -0.0940 0.5500 1.0000
3.750 0.9425 0.01964 0.01037 -0.0937 0.5414 1.0000
4.000 0.9669 0.02010 0.01080 -0.0932 0.5313 1.0000
4.250 0.9942 0.02041 0.01095 -0.0930 0.5240 1.0000
4.500 1.0182 0.02093 0.01151 -0.0926 0.5147 1.0000
4.750 1.0448 0.02131 0.01180 -0.0924 0.5079 1.0000
5.000 1.0690 0.02183 0.01237 -0.0920 0.4993 1.0000
5.250 1.0957 0.02223 0.01268 -0.0918 0.4930 1.0000
5.500 1.1190 0.02286 0.01344 -0.0914 0.4851 1.0000
5.750 1.1466 0.02326 0.01375 -0.0914 0.4798 1.0000
6.000 1.1684 0.02406 0.01471 -0.0908 0.4724 1.0000
6.250 1.1947 0.02452 0.01516 -0.0907 0.4665 1.0000
6.500 1.2183 0.02526 0.01600 -0.0903 0.4606 1.0000
6.750 1.2413 0.02603 0.01690 -0.0899 0.4545 1.0000
7.000 1.2684 0.02657 0.01742 -0.0899 0.4500 1.0000
7.250 1.2884 0.02763 0.01869 -0.0892 0.4441 1.0000
7.500 1.3112 0.02842 0.01963 -0.0888 0.4385 1.0000
7.750 1.3390 0.02897 0.02018 -0.0889 0.4344 1.0000
8.000 1.3551 0.03040 0.02191 -0.0879 0.4290 1.0000
8.250 1.3758 0.03144 0.02313 -0.0873 0.4239 1.0000
8.500 1.4060 0.03153 0.02318 -0.0874 0.4178 1.0000
8.750 1.4228 0.03201 0.02387 -0.0859 0.4074 1.0000
9.000 1.4452 0.03181 0.02372 -0.0848 0.3955 1.0000
9.250 1.4716 0.03148 0.02338 -0.0842 0.3849 1.0000
9.500 1.4986 0.03094 0.02277 -0.0836 0.3730 1.0000
9.750 1.5134 0.03100 0.02304 -0.0816 0.3604 1.0000
10.000 1.5303 0.03064 0.02276 -0.0797 0.3455 1.0000
10.250 1.5448 0.03016 0.02234 -0.0774 0.3287 1.0000
10.500 1.5474 0.03011 0.02247 -0.0737 0.3086 1.0000
10.750 1.5439 0.03037 0.02286 -0.0694 0.2850 1.0000
11.000 1.5338 0.03133 0.02394 -0.0646 0.2579 1.0000
11.250 1.5191 0.03332 0.02587 -0.0606 0.2143 1.0000
11.500 1.4954 0.03686 0.02902 -0.0573 0.1529 1.0000
11.750 1.4679 0.04158 0.03340 -0.0550 0.1140 1.0000
12.000 1.4433 0.04669 0.03838 -0.0539 0.0951 1.0000
12.250 1.4212 0.05205 0.04375 -0.0536 0.0848 1.0000
12.500 1.4009 0.05760 0.04938 -0.0538 0.0782 1.0000
12.750 1.3806 0.06341 0.05531 -0.0545 0.0741 1.0000
13.000 1.3596 0.06954 0.06154 -0.0555 0.0717 1.0000
13.250 1.3418 0.07548 0.06761 -0.0566 0.0690 1.0000
13.500 1.3258 0.08130 0.07357 -0.0577 0.0665 1.0000
13.750 1.3109 0.08703 0.07941 -0.0589 0.0642 1.0000
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Polar data table (+)
Polar graphs
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