GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 380 AIRFOIL (goe380-il) Reynolds number: 500,000 Max Cl/Cd: 103.17 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe380-il-500000-n5.txt Download as CSV file: xf-goe380-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 380 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2749 0.10805 0.10588 -0.0267 1.0000 0.0052
-8.750 -0.2727 0.10565 0.10352 -0.0266 1.0000 0.0052
-8.500 -0.2714 0.10337 0.10126 -0.0263 1.0000 0.0052
-8.250 -0.2570 0.09857 0.09648 -0.0289 0.9976 0.0053
-8.000 -0.2430 0.09491 0.09283 -0.0317 0.9927 0.0054
-7.750 -0.2285 0.09150 0.08942 -0.0348 0.9879 0.0055
-7.500 -0.2145 0.08822 0.08615 -0.0380 0.9811 0.0056
-7.250 -0.1994 0.08489 0.08282 -0.0416 0.9740 0.0058
-7.000 -0.1801 0.08127 0.07920 -0.0466 0.9672 0.0058
-6.750 -0.1576 0.07741 0.07533 -0.0523 0.9590 0.0060
-6.500 -0.1317 0.07350 0.07139 -0.0587 0.9512 0.0061
-6.250 -0.1052 0.06965 0.06751 -0.0649 0.9413 0.0064
-6.000 -0.0785 0.06587 0.06368 -0.0708 0.9279 0.0068
-5.750 -0.0525 0.06227 0.06001 -0.0761 0.9094 0.0072
-5.500 -0.0269 0.05898 0.05662 -0.0806 0.8870 0.0077
-5.250 -0.0015 0.05611 0.05361 -0.0845 0.8644 0.0080
-5.000 0.0219 0.05330 0.05065 -0.0873 0.8434 0.0082
-4.750 0.0434 0.05040 0.04762 -0.0894 0.8255 0.0082
-4.500 0.0663 0.04745 0.04453 -0.0913 0.8083 0.0083
-4.250 0.0898 0.04444 0.04137 -0.0929 0.7912 0.0083
-2.750 0.2326 0.02713 0.02283 -0.0968 0.6717 0.0076
-2.500 0.2575 0.02446 0.01985 -0.0965 0.6498 0.0071
-2.250 0.2831 0.02166 0.01671 -0.0957 0.6300 0.0068
-1.750 0.3334 0.01380 0.00770 -0.0927 0.5983 0.0063
-1.500 0.3587 0.01234 0.00582 -0.0918 0.5838 0.0067
-1.250 0.3845 0.01156 0.00476 -0.0911 0.5708 0.0075
-1.000 0.4103 0.01113 0.00413 -0.0905 0.5590 0.0086
-0.750 0.4352 0.01031 0.00308 -0.0897 0.5481 0.0095
-0.500 0.4606 0.00998 0.00261 -0.0891 0.5380 0.0107
-0.250 0.4864 0.00977 0.00230 -0.0885 0.5285 0.0128
0.000 0.5123 0.00965 0.00207 -0.0880 0.5205 0.0156
0.250 0.5381 0.00948 0.00183 -0.0874 0.5123 0.0260
0.500 0.5641 0.00944 0.00184 -0.0871 0.5047 0.0566
0.750 0.5904 0.00951 0.00188 -0.0868 0.4964 0.0696
1.000 0.6170 0.00959 0.00194 -0.0865 0.4878 0.0798
1.250 0.6431 0.00964 0.00192 -0.0861 0.4783 0.0843
1.500 0.6689 0.00967 0.00190 -0.0857 0.4670 0.0892
1.750 0.6950 0.00972 0.00191 -0.0854 0.4556 0.0951
2.000 0.7208 0.00980 0.00192 -0.0850 0.4418 0.0992
2.250 0.7462 0.00985 0.00194 -0.0846 0.4269 0.1043
2.500 0.7714 0.00997 0.00197 -0.0841 0.4093 0.1088
2.750 0.7965 0.01010 0.00203 -0.0837 0.3932 0.1146
3.000 0.8214 0.01023 0.00211 -0.0832 0.3770 0.1215
3.250 0.8462 0.01038 0.00222 -0.0827 0.3621 0.1343
3.750 0.9251 0.00931 0.00273 -0.0889 0.3378 1.0000
4.000 0.9493 0.00948 0.00287 -0.0882 0.3308 1.0000
4.250 0.9734 0.00967 0.00302 -0.0876 0.3238 1.0000
4.500 0.9974 0.00985 0.00318 -0.0869 0.3173 1.0000
4.750 1.0214 0.01005 0.00338 -0.0862 0.3098 1.0000
5.000 1.0453 0.01025 0.00357 -0.0856 0.3032 1.0000
5.250 1.0695 0.01043 0.00377 -0.0850 0.2970 1.0000
5.500 1.0931 0.01065 0.00400 -0.0843 0.2908 1.0000
5.750 1.1173 0.01083 0.00422 -0.0837 0.2836 1.0000
6.000 1.1407 0.01107 0.00446 -0.0830 0.2759 1.0000
6.250 1.1635 0.01135 0.00472 -0.0822 0.2587 1.0000
6.500 1.1834 0.01188 0.00507 -0.0810 0.2197 1.0000
6.750 1.1994 0.01275 0.00562 -0.0793 0.1674 1.0000
7.000 1.2163 0.01355 0.00622 -0.0777 0.1317 1.0000
7.250 1.2175 0.01573 0.00771 -0.0737 0.0198 1.0000
7.500 1.2355 0.01640 0.00840 -0.0721 0.0092 1.0000
7.750 1.2543 0.01698 0.00909 -0.0707 0.0068 1.0000
8.000 1.2722 0.01760 0.00982 -0.0692 0.0054 1.0000
8.250 1.2891 0.01828 0.01061 -0.0675 0.0046 1.0000
8.500 1.3049 0.01901 0.01145 -0.0657 0.0042 1.0000
8.750 1.3192 0.01980 0.01233 -0.0636 0.0037 1.0000
9.000 1.3296 0.02072 0.01336 -0.0610 0.0035 1.0000
9.250 1.3328 0.02193 0.01470 -0.0571 0.0032 1.0000
9.500 1.3412 0.02282 0.01570 -0.0543 0.0030 1.0000
9.750 1.3445 0.02405 0.01706 -0.0509 0.0029 1.0000
10.000 1.3535 0.02497 0.01806 -0.0486 0.0025 1.0000
10.250 1.3540 0.02649 0.01971 -0.0454 0.0024 1.0000
10.500 1.3590 0.02778 0.02109 -0.0431 0.0022 1.0000
10.750 1.3584 0.02957 0.02302 -0.0406 0.0021 1.0000
11.000 1.3551 0.03175 0.02533 -0.0382 0.0021 1.0000
11.250 1.3474 0.03451 0.02822 -0.0361 0.0020 1.0000
11.500 1.3435 0.03717 0.03101 -0.0346 0.0020 1.0000
11.750 1.3419 0.03982 0.03382 -0.0334 0.0018 1.0000
12.000 1.3371 0.04295 0.03710 -0.0325 0.0018 1.0000
12.250 1.3337 0.04606 0.04035 -0.0319 0.0017 1.0000
12.500 1.3279 0.04961 0.04405 -0.0312 0.0016 1.0000
12.750 1.3240 0.05304 0.04763 -0.0307 0.0016 1.0000
13.000 1.3218 0.05633 0.05104 -0.0306 0.0017 1.0000
13.250 1.3188 0.05981 0.05467 -0.0303 0.0016 1.0000
13.500 1.3149 0.06356 0.05858 -0.0300 0.0016 1.0000
13.750 1.3103 0.06757 0.06277 -0.0298 0.0015 1.0000
14.000 1.3058 0.07164 0.06702 -0.0302 0.0015 1.0000
14.250 1.2996 0.07616 0.07171 -0.0307 0.0015 1.0000
14.500 1.2921 0.08099 0.07672 -0.0318 0.0015 1.0000
14.750 1.2821 0.08642 0.08235 -0.0333 0.0015 1.0000
15.000 1.2715 0.09212 0.08823 -0.0352 0.0015 1.0000
15.250 1.2610 0.09796 0.09423 -0.0375 0.0016 1.0000
15.500 1.2480 0.10450 0.10095 -0.0403 0.0015 1.0000
15.750 1.2363 0.11099 0.10760 -0.0435 0.0016 1.0000
16.000 1.2246 0.11773 0.11449 -0.0470 0.0016 1.0000
16.250 1.2113 0.12504 0.12197 -0.0509 0.0016 1.0000
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Polar data table (+)
Polar graphs
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