GOE 387 AIRFOIL (goe387-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 387 AIRFOIL (goe387-il) Reynolds number: 50,000 Max Cl/Cd: 22.6 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe387-il-50000-n5.txt Download as CSV file: xf-goe387-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 387 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1551 0.11253 0.10588 -0.0584 0.9545 0.1462
-8.750 -0.1610 0.11065 0.10403 -0.0652 0.9437 0.1494
-8.500 -0.1604 0.10795 0.10135 -0.0695 0.9323 0.1498
-8.250 -0.1401 0.10329 0.09669 -0.0731 0.9269 0.1504
-7.750 -0.1115 0.08964 0.08283 -0.0818 0.9114 0.0902
-7.250 -0.1122 0.07995 0.07307 -0.0919 0.8910 0.0811
-7.000 -0.1083 0.07754 0.07066 -0.0918 0.8799 0.0799
-6.750 -0.0959 0.07347 0.06652 -0.0954 0.8732 0.0780
-6.500 -0.1014 0.07022 0.06321 -0.0960 0.8612 0.0763
-6.250 -0.1085 0.06237 0.05489 -0.1020 0.8532 0.0722
-6.000 -0.1107 0.06053 0.05297 -0.0998 0.8417 0.0718
-5.750 -0.0946 0.05710 0.04932 -0.1014 0.8360 0.0711
-5.500 -0.0937 0.05498 0.04702 -0.0995 0.8259 0.0706
-5.250 -0.0797 0.05192 0.04365 -0.0999 0.8194 0.0701
-5.000 -0.0663 0.04925 0.04063 -0.0995 0.8127 0.0700
-4.750 -0.0586 0.04733 0.03839 -0.0977 0.8037 0.0702
-4.500 -0.0353 0.04475 0.03533 -0.0981 0.7989 0.0709
-4.250 -0.0265 0.04336 0.03358 -0.0957 0.7900 0.0715
-4.000 -0.0057 0.04165 0.03145 -0.0950 0.7835 0.0720
-3.750 0.0255 0.03974 0.02912 -0.0955 0.7794 0.0724
-3.500 0.0342 0.03913 0.02834 -0.0927 0.7696 0.0727
-3.250 0.0619 0.03789 0.02690 -0.0926 0.7640 0.0734
-3.000 0.0976 0.03654 0.02534 -0.0935 0.7602 0.0744
-2.750 0.1046 0.03641 0.02511 -0.0903 0.7496 0.0751
-2.500 0.1371 0.03542 0.02396 -0.0907 0.7445 0.0772
-2.250 0.1604 0.03491 0.02328 -0.0897 0.7375 0.0798
-2.000 0.1817 0.03452 0.02276 -0.0884 0.7293 0.0824
-1.750 0.2192 0.03364 0.02181 -0.0895 0.7248 0.0861
-1.500 0.2338 0.03367 0.02176 -0.0874 0.7150 0.0888
-1.250 0.2658 0.03309 0.02102 -0.0876 0.7089 0.0930
-1.000 0.3063 0.03221 0.02007 -0.0889 0.7050 0.1013
-0.750 0.3121 0.03262 0.02051 -0.0857 0.6932 0.1084
-0.500 0.3498 0.03171 0.01972 -0.0867 0.6885 0.1384
-0.250 0.3619 0.03167 0.02007 -0.0846 0.6784 0.2062
0.000 0.3906 0.03066 0.01984 -0.0845 0.6723 0.4029
0.250 0.4985 0.02853 0.01896 -0.0975 0.6693 1.0000
0.500 0.5017 0.02938 0.01964 -0.0938 0.6580 1.0000
0.750 0.5346 0.02923 0.01919 -0.0940 0.6524 1.0000
1.000 0.5422 0.02998 0.01978 -0.0909 0.6420 1.0000
1.250 0.5703 0.03002 0.01959 -0.0905 0.6356 1.0000
1.500 0.5866 0.03051 0.01991 -0.0886 0.6271 1.0000
1.750 0.6061 0.03086 0.02010 -0.0871 0.6188 1.0000
2.000 0.6436 0.03057 0.01958 -0.0879 0.6144 1.0000
2.250 0.6413 0.03179 0.02075 -0.0837 0.6023 1.0000
2.500 0.6764 0.03157 0.02035 -0.0842 0.5974 1.0000
2.750 0.6760 0.03279 0.02152 -0.0804 0.5860 1.0000
3.000 0.7074 0.03272 0.02130 -0.0804 0.5806 1.0000
3.250 0.7104 0.03388 0.02241 -0.0771 0.5704 1.0000
3.500 0.7356 0.03408 0.02250 -0.0765 0.5641 1.0000
4.000 0.7598 0.03561 0.02390 -0.0721 0.5478 1.0000
4.250 0.7979 0.03530 0.02347 -0.0729 0.5439 1.0000
4.500 0.7809 0.03750 0.02568 -0.0678 0.5321 1.0000
4.750 0.8134 0.03739 0.02549 -0.0679 0.5279 1.0000
5.250 0.8280 0.03981 0.02785 -0.0634 0.5120 1.0000
5.500 0.8663 0.03934 0.02731 -0.0639 0.5091 1.0000
6.000 0.8716 0.04267 0.03065 -0.0593 0.4933 1.0000
6.500 0.8756 0.04661 0.03459 -0.0555 0.4776 1.0000
6.750 0.9117 0.04603 0.03398 -0.0554 0.4753 1.0000
7.250 0.9077 0.05104 0.03905 -0.0519 0.4593 1.0000
7.750 0.9103 0.05573 0.04380 -0.0493 0.4431 1.0000
8.250 0.9245 0.05909 0.04718 -0.0469 0.4268 1.0000
8.500 0.9695 0.05675 0.04481 -0.0462 0.4246 1.0000
9.000 0.9602 0.06275 0.05090 -0.0438 0.4058 1.0000
9.500 0.9410 0.07075 0.05902 -0.0426 0.3864 1.0000
10.000 0.9680 0.07321 0.06156 -0.0411 0.3748 1.0000
11.000 0.9666 0.08541 0.07401 -0.0396 0.3413 1.0000
11.250 0.9960 0.08444 0.07308 -0.0384 0.3390 1.0000
11.750 0.9753 0.09386 0.08263 -0.0390 0.3198 1.0000
12.250 0.9818 0.09948 0.08839 -0.0388 0.3057 1.0000
12.750 0.9697 0.10832 0.09734 -0.0400 0.2901 1.0000
13.250 0.9521 0.11850 0.10765 -0.0422 0.2758 1.0000
13.500 0.9745 0.11856 0.10779 -0.0414 0.2733 1.0000
14.000 0.9551 0.12929 0.11865 -0.0443 0.2599 1.0000
14.250 0.9545 0.13316 0.12257 -0.0453 0.2547 1.0000
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Polar data table (+)
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