GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 385 AIRFOIL (goe385-il) Reynolds number: 50,000 Max Cl/Cd: 37.49 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe385-il-50000-n5.txt Download as CSV file: xf-goe385-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 385 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3504 0.10535 0.09882 -0.0270 1.0000 0.1039
-8.250 -0.3638 0.10414 0.09777 -0.0307 1.0000 0.1054
-8.000 -0.3592 0.09995 0.09367 -0.0310 1.0000 0.1070
-7.750 -0.3431 0.09565 0.08937 -0.0282 1.0000 0.1117
-7.500 -0.3441 0.09303 0.08685 -0.0291 1.0000 0.1162
-7.250 -0.3579 0.09163 0.08558 -0.0352 1.0000 0.1207
-7.000 -0.3523 0.08754 0.08159 -0.0328 1.0000 0.1234
-6.750 -0.3476 0.08477 0.07889 -0.0305 1.0000 0.1301
-6.250 -0.3535 0.07974 0.07404 -0.0301 1.0000 0.1425
-6.000 -0.3633 0.07845 0.07271 -0.0345 1.0000 0.1522
-5.750 -0.3596 0.07513 0.06955 -0.0287 1.0000 0.1576
-5.500 -0.3567 0.07247 0.06688 -0.0306 0.9980 0.1698
-5.000 -0.2588 0.05810 0.05126 -0.0531 0.9771 0.0901
-4.750 -0.2287 0.05357 0.04666 -0.0561 0.9681 0.0871
-4.500 -0.1876 0.04829 0.04069 -0.0617 0.9584 0.0769
-4.250 -0.1478 0.04463 0.03657 -0.0656 0.9506 0.0735
-4.000 -0.1112 0.04179 0.03307 -0.0685 0.9397 0.0749
-3.750 -0.0750 0.03898 0.02979 -0.0710 0.9300 0.0748
-3.500 -0.0358 0.03626 0.02664 -0.0739 0.9221 0.0742
-3.250 -0.0021 0.03419 0.02417 -0.0753 0.9111 0.0740
-3.000 0.0335 0.03241 0.02195 -0.0769 0.9013 0.0763
-2.750 0.0697 0.03066 0.02000 -0.0788 0.8928 0.0788
-2.500 0.1025 0.02935 0.01836 -0.0795 0.8818 0.0791
-2.250 0.1363 0.02818 0.01693 -0.0803 0.8720 0.0797
-2.000 0.1725 0.02707 0.01558 -0.0813 0.8639 0.0808
-1.750 0.2030 0.02629 0.01462 -0.0813 0.8529 0.0822
-1.500 0.2344 0.02566 0.01381 -0.0815 0.8426 0.0862
-1.250 0.2670 0.02507 0.01301 -0.0818 0.8335 0.0911
-1.000 0.2962 0.02447 0.01235 -0.0818 0.8228 0.0949
-0.750 0.3241 0.02408 0.01183 -0.0815 0.8111 0.0988
-0.500 0.3524 0.02375 0.01134 -0.0812 0.7994 0.1042
-0.250 0.3809 0.02335 0.01089 -0.0809 0.7876 0.1132
0.000 0.4097 0.02288 0.01046 -0.0806 0.7761 0.1372
0.500 0.4648 0.02055 0.01012 -0.0793 0.7502 1.0000
0.750 0.4906 0.02073 0.01004 -0.0786 0.7374 1.0000
1.000 0.5165 0.02091 0.01000 -0.0779 0.7250 1.0000
1.250 0.5426 0.02106 0.00995 -0.0773 0.7130 1.0000
1.500 0.5694 0.02118 0.00989 -0.0767 0.7016 1.0000
1.750 0.5950 0.02136 0.00994 -0.0760 0.6890 1.0000
2.000 0.6205 0.02157 0.01003 -0.0754 0.6762 1.0000
2.250 0.6461 0.02178 0.01014 -0.0748 0.6636 1.0000
2.500 0.6719 0.02199 0.01026 -0.0741 0.6511 1.0000
2.750 0.6980 0.02221 0.01038 -0.0735 0.6386 1.0000
3.000 0.7243 0.02243 0.01051 -0.0729 0.6262 1.0000
3.250 0.7503 0.02267 0.01071 -0.0723 0.6136 1.0000
3.500 0.7752 0.02301 0.01101 -0.0717 0.5996 1.0000
3.750 0.7998 0.02338 0.01137 -0.0711 0.5857 1.0000
4.000 0.8243 0.02376 0.01178 -0.0704 0.5717 1.0000
4.250 0.8485 0.02416 0.01219 -0.0698 0.5577 1.0000
4.500 0.8727 0.02457 0.01262 -0.0692 0.5439 1.0000
4.750 0.8968 0.02499 0.01310 -0.0685 0.5304 1.0000
5.000 0.9209 0.02542 0.01357 -0.0679 0.5173 1.0000
5.250 0.9452 0.02584 0.01403 -0.0673 0.5050 1.0000
5.500 0.9700 0.02623 0.01448 -0.0667 0.4936 1.0000
5.750 0.9929 0.02680 0.01515 -0.0660 0.4811 1.0000
6.000 1.0160 0.02738 0.01583 -0.0654 0.4693 1.0000
6.250 1.0396 0.02794 0.01648 -0.0648 0.4587 1.0000
6.500 1.0648 0.02840 0.01701 -0.0643 0.4496 1.0000
6.750 1.0864 0.02917 0.01795 -0.0636 0.4386 1.0000
7.000 1.1088 0.02983 0.01873 -0.0629 0.4280 1.0000
7.250 1.1322 0.03035 0.01932 -0.0622 0.4176 1.0000
7.500 1.1544 0.03090 0.02001 -0.0613 0.4061 1.0000
7.750 1.1740 0.03159 0.02086 -0.0603 0.3935 1.0000
8.000 1.1937 0.03231 0.02173 -0.0592 0.3815 1.0000
8.250 1.2145 0.03304 0.02260 -0.0583 0.3712 1.0000
8.500 1.2364 0.03380 0.02357 -0.0575 0.3624 1.0000
8.750 1.2542 0.03491 0.02496 -0.0565 0.3531 1.0000
9.000 1.2760 0.03570 0.02591 -0.0557 0.3445 1.0000
9.250 1.2930 0.03669 0.02715 -0.0544 0.3338 1.0000
9.500 1.3068 0.03764 0.02833 -0.0527 0.3210 1.0000
9.750 1.3181 0.03834 0.02921 -0.0506 0.3053 1.0000
10.000 1.3256 0.03893 0.02986 -0.0481 0.2875 1.0000
10.250 1.3243 0.04011 0.03120 -0.0450 0.2698 1.0000
10.500 1.3205 0.04146 0.03272 -0.0419 0.2541 1.0000
10.750 1.3167 0.04309 0.03450 -0.0392 0.2398 1.0000
11.000 1.3111 0.04516 0.03674 -0.0370 0.2246 1.0000
11.250 1.3025 0.04781 0.03958 -0.0356 0.2063 1.0000
11.500 1.2927 0.05093 0.04279 -0.0348 0.1855 1.0000
11.750 1.2821 0.05462 0.04655 -0.0346 0.1623 1.0000
12.000 1.2700 0.05871 0.05054 -0.0348 0.1411 1.0000
12.250 1.2562 0.06334 0.05507 -0.0353 0.1244 1.0000
12.500 1.2413 0.06842 0.06012 -0.0361 0.1103 1.0000
12.750 1.2263 0.07380 0.06556 -0.0372 0.0966 1.0000
13.000 1.2115 0.07937 0.07121 -0.0386 0.0830 1.0000
13.250 1.1963 0.08509 0.07692 -0.0401 0.0740 1.0000
13.500 1.1813 0.09091 0.08267 -0.0418 0.0683 1.0000
13.750 1.1688 0.09648 0.08823 -0.0434 0.0634 1.0000
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Polar data table (+)
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