GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 361 AIRFOIL (goe361-il) Reynolds number: 50,000 Max Cl/Cd: 42.38 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe361-il-50000-n5.txt Download as CSV file: xf-goe361-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 361 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2821 0.10937 0.10269 -0.0261 1.0000 0.0705
-8.000 -0.2893 0.10935 0.10282 -0.0267 1.0000 0.0714
-7.750 -0.2957 0.10926 0.10289 -0.0282 1.0000 0.0718
-7.500 -0.2763 0.10132 0.09493 -0.0249 1.0000 0.0754
-7.250 -0.2743 0.09891 0.09261 -0.0240 1.0000 0.0783
-7.000 -0.2749 0.09701 0.09082 -0.0236 1.0000 0.0813
-6.750 -0.2762 0.09566 0.08959 -0.0246 1.0000 0.0840
-6.500 -0.2772 0.09523 0.08928 -0.0280 1.0000 0.0856
-6.250 -0.2732 0.09474 0.08886 -0.0333 1.0000 0.0863
-6.000 -0.2725 0.08912 0.08333 -0.0269 1.0000 0.0880
-5.750 -0.2703 0.08612 0.08040 -0.0245 1.0000 0.0906
-5.500 -0.2680 0.08390 0.07824 -0.0240 1.0000 0.0939
-5.250 -0.2627 0.08227 0.07666 -0.0267 1.0000 0.0989
-5.000 -0.2499 0.08065 0.07505 -0.0331 1.0000 0.1016
-4.750 -0.2540 0.07719 0.07171 -0.0275 1.0000 0.1046
-4.250 -0.1853 0.06911 0.06347 -0.0415 0.9830 0.1199
-4.000 -0.1345 0.06512 0.05925 -0.0534 0.9719 0.1313
-3.750 -0.0969 0.06121 0.05523 -0.0594 0.9615 0.1461
-3.500 -0.0608 0.05735 0.05131 -0.0641 0.9517 0.1623
-3.250 -0.0238 0.05390 0.04774 -0.0691 0.9399 0.1782
-3.000 0.0156 0.05083 0.04451 -0.0744 0.9284 0.2004
-2.500 0.1458 0.04139 0.03387 -0.0942 0.9105 0.0978
-2.250 0.1947 0.03801 0.02996 -0.0993 0.9002 0.0840
-2.000 0.2390 0.03524 0.02686 -0.1032 0.8910 0.0800
-1.750 0.2813 0.03287 0.02402 -0.1063 0.8797 0.0766
-1.500 0.3188 0.03113 0.02191 -0.1082 0.8668 0.0778
-1.250 0.3554 0.02963 0.02005 -0.1098 0.8537 0.0799
-1.000 0.3911 0.02818 0.01820 -0.1109 0.8402 0.0792
-0.750 0.4259 0.02691 0.01658 -0.1117 0.8262 0.0785
-0.500 0.4590 0.02584 0.01519 -0.1120 0.8116 0.0784
-0.250 0.4909 0.02492 0.01396 -0.1120 0.7965 0.0787
0.000 0.5239 0.02412 0.01285 -0.1121 0.7809 0.0796
0.250 0.5559 0.02343 0.01188 -0.1119 0.7645 0.0811
0.500 0.5868 0.02286 0.01106 -0.1115 0.7476 0.0843
0.750 0.6153 0.02239 0.01047 -0.1110 0.7289 0.0910
1.000 0.6431 0.02207 0.00998 -0.1103 0.7095 0.0984
1.250 0.6713 0.02175 0.00954 -0.1097 0.6907 0.1056
1.500 0.6997 0.02150 0.00917 -0.1092 0.6724 0.1194
1.750 0.7272 0.02038 0.00915 -0.1093 0.6539 0.4398
2.250 0.7780 0.02013 0.00890 -0.1070 0.6173 1.0000
2.500 0.8037 0.02043 0.00896 -0.1062 0.5998 1.0000
2.750 0.8292 0.02076 0.00908 -0.1055 0.5827 1.0000
3.000 0.8542 0.02112 0.00930 -0.1047 0.5656 1.0000
3.250 0.8789 0.02150 0.00959 -0.1040 0.5484 1.0000
3.500 0.9037 0.02190 0.00989 -0.1033 0.5322 1.0000
3.750 0.9285 0.02232 0.01023 -0.1026 0.5167 1.0000
4.000 0.9532 0.02277 0.01064 -0.1019 0.5020 1.0000
4.250 0.9779 0.02324 0.01105 -0.1012 0.4878 1.0000
4.500 1.0025 0.02373 0.01150 -0.1005 0.4745 1.0000
4.750 1.0273 0.02424 0.01197 -0.0999 0.4621 1.0000
5.000 1.0518 0.02482 0.01259 -0.0993 0.4501 1.0000
5.250 1.0760 0.02546 0.01330 -0.0987 0.4389 1.0000
5.500 1.1007 0.02612 0.01401 -0.0982 0.4295 1.0000
5.750 1.1255 0.02679 0.01478 -0.0977 0.4206 1.0000
6.000 1.1492 0.02757 0.01571 -0.0971 0.4116 1.0000
6.250 1.1744 0.02826 0.01646 -0.0967 0.4043 1.0000
6.500 1.1969 0.02917 0.01760 -0.0960 0.3960 1.0000
6.750 1.2219 0.02993 0.01853 -0.0956 0.3899 1.0000
7.000 1.2440 0.03097 0.01987 -0.0949 0.3835 1.0000
7.250 1.2674 0.03195 0.02110 -0.0944 0.3780 1.0000
7.500 1.2868 0.03252 0.02188 -0.0930 0.3654 1.0000
7.750 1.3022 0.03237 0.02176 -0.0907 0.3431 1.0000
8.000 1.3149 0.03272 0.02232 -0.0884 0.3228 1.0000
8.250 1.3255 0.03299 0.02264 -0.0858 0.2997 1.0000
8.500 1.3365 0.03366 0.02358 -0.0835 0.2793 1.0000
8.750 1.3420 0.03446 0.02447 -0.0806 0.2490 1.0000
9.000 1.3444 0.03571 0.02574 -0.0776 0.2081 1.0000
9.250 1.3329 0.03819 0.02756 -0.0740 0.1061 1.0000
9.500 1.3156 0.04195 0.03083 -0.0707 0.0683 1.0000
9.750 1.3067 0.04525 0.03413 -0.0686 0.0595 1.0000
10.000 1.2969 0.04884 0.03778 -0.0671 0.0549 1.0000
10.250 1.2879 0.05262 0.04175 -0.0663 0.0518 1.0000
10.500 1.2774 0.05690 0.04627 -0.0663 0.0496 1.0000
10.750 1.2654 0.06171 0.05127 -0.0670 0.0479 1.0000
11.000 1.2523 0.06701 0.05673 -0.0682 0.0466 1.0000
11.250 1.2392 0.07256 0.06244 -0.0697 0.0456 1.0000
11.500 1.2279 0.07799 0.06800 -0.0712 0.0447 1.0000
11.750 1.2194 0.08307 0.07326 -0.0726 0.0437 1.0000
12.000 1.2122 0.08794 0.07830 -0.0738 0.0428 1.0000
12.250 1.2067 0.09249 0.08299 -0.0748 0.0419 1.0000
12.500 1.2033 0.09663 0.08727 -0.0755 0.0410 1.0000
12.750 1.2020 0.10041 0.09116 -0.0759 0.0399 1.0000
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Polar data table (+)
Polar graphs
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