GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 363 AIRFOIL (goe363-il) Reynolds number: 50,000 Max Cl/Cd: 37.01 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe363-il-50000-n5.txt Download as CSV file: xf-goe363-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 363 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3074 0.10855 0.10290 -0.0198 1.0000 0.1106
-7.250 -0.3183 0.10714 0.10158 -0.0175 1.0000 0.1114
-7.000 -0.3299 0.10571 0.10025 -0.0153 1.0000 0.1121
-6.750 -0.3129 0.10162 0.09615 -0.0206 0.9926 0.1134
-6.500 -0.2929 0.09303 0.08741 -0.0402 0.9788 0.0793
-6.250 -0.2713 0.08877 0.08313 -0.0406 0.9735 0.0778
-6.000 -0.2523 0.08446 0.07880 -0.0442 0.9658 0.0756
-5.500 -0.2005 0.07141 0.06543 -0.0631 0.9497 0.0660
-5.250 -0.1751 0.06601 0.05983 -0.0695 0.9414 0.0664
-5.000 -0.1502 0.06361 0.05743 -0.0712 0.9352 0.0694
-4.750 -0.1211 0.05862 0.05219 -0.0768 0.9274 0.0694
-4.500 -0.0853 0.05306 0.04627 -0.0833 0.9208 0.0691
-4.250 -0.0525 0.05000 0.04297 -0.0870 0.9141 0.0724
-4.000 -0.0174 0.04582 0.03833 -0.0914 0.9067 0.0747
-3.750 0.0273 0.04134 0.03319 -0.0969 0.9023 0.0758
-3.500 0.0602 0.03795 0.02901 -0.0993 0.8940 0.0792
-3.000 0.1298 0.03484 0.02540 -0.1028 0.8795 0.0860
-2.750 0.1712 0.03295 0.02299 -0.1053 0.8739 0.0901
-2.500 0.2017 0.03205 0.02189 -0.1059 0.8648 0.0960
-2.250 0.2421 0.03105 0.02057 -0.1078 0.8587 0.1057
-2.000 0.2705 0.03044 0.01991 -0.1077 0.8486 0.1133
-1.750 0.3116 0.02950 0.01875 -0.1094 0.8428 0.1302
-1.500 0.3399 0.02905 0.01823 -0.1092 0.8316 0.1576
-1.250 0.3730 0.02846 0.01757 -0.1096 0.8204 0.1954
-1.000 0.4076 0.02793 0.01717 -0.1101 0.8077 0.2479
-0.750 0.4428 0.02712 0.01633 -0.1103 0.7941 0.2859
-0.500 0.4762 0.02627 0.01543 -0.1100 0.7800 0.3118
-0.250 0.5046 0.02563 0.01480 -0.1092 0.7645 0.3398
0.000 0.5312 0.02501 0.01435 -0.1084 0.7495 0.3843
0.500 0.5802 0.02310 0.01356 -0.1052 0.7193 1.0000
0.750 0.6068 0.02307 0.01325 -0.1043 0.7037 1.0000
1.000 0.6334 0.02304 0.01297 -0.1035 0.6878 1.0000
1.250 0.6604 0.02299 0.01269 -0.1026 0.6715 1.0000
1.500 0.6852 0.02305 0.01257 -0.1016 0.6531 1.0000
1.750 0.7115 0.02307 0.01240 -0.1008 0.6349 1.0000
2.000 0.7387 0.02306 0.01219 -0.1000 0.6163 1.0000
2.250 0.7667 0.02305 0.01195 -0.0993 0.5974 1.0000
2.500 0.7934 0.02316 0.01184 -0.0985 0.5777 1.0000
2.750 0.8191 0.02337 0.01185 -0.0977 0.5573 1.0000
3.000 0.8448 0.02365 0.01191 -0.0969 0.5376 1.0000
3.250 0.8701 0.02400 0.01204 -0.0961 0.5182 1.0000
3.500 0.8937 0.02446 0.01233 -0.0952 0.4984 1.0000
3.750 0.9163 0.02499 0.01273 -0.0943 0.4789 1.0000
4.000 0.9390 0.02554 0.01316 -0.0934 0.4609 1.0000
4.250 0.9617 0.02611 0.01362 -0.0925 0.4447 1.0000
4.500 0.9848 0.02670 0.01411 -0.0918 0.4304 1.0000
4.750 1.0082 0.02730 0.01463 -0.0911 0.4180 1.0000
5.000 1.0322 0.02789 0.01511 -0.0905 0.4069 1.0000
5.250 1.0548 0.02856 0.01577 -0.0898 0.3956 1.0000
5.500 1.0779 0.02922 0.01640 -0.0892 0.3855 1.0000
5.750 1.1021 0.02983 0.01689 -0.0887 0.3766 1.0000
6.000 1.1237 0.03059 0.01770 -0.0880 0.3670 1.0000
6.250 1.1467 0.03127 0.01834 -0.0873 0.3585 1.0000
6.500 1.1678 0.03199 0.01905 -0.0865 0.3490 1.0000
6.750 1.1873 0.03278 0.01986 -0.0855 0.3395 1.0000
7.000 1.2092 0.03345 0.02041 -0.0847 0.3307 1.0000
7.250 1.2261 0.03434 0.02146 -0.0834 0.3215 1.0000
7.500 1.2473 0.03512 0.02221 -0.0827 0.3140 1.0000
7.750 1.2650 0.03608 0.02331 -0.0816 0.3066 1.0000
8.250 1.3032 0.03801 0.02545 -0.0798 0.2939 1.0000
8.500 1.3229 0.03895 0.02645 -0.0789 0.2879 1.0000
8.750 1.3419 0.04000 0.02760 -0.0780 0.2824 1.0000
9.000 1.3552 0.04131 0.02913 -0.0766 0.2766 1.0000
9.250 1.3746 0.04235 0.03028 -0.0758 0.2715 1.0000
9.500 1.3915 0.04359 0.03166 -0.0747 0.2667 1.0000
9.750 1.3986 0.04522 0.03357 -0.0727 0.2614 1.0000
10.000 1.4128 0.04651 0.03500 -0.0714 0.2567 1.0000
10.250 1.4371 0.04753 0.03603 -0.0712 0.2526 1.0000
10.500 1.4303 0.04987 0.03878 -0.0680 0.2482 1.0000
10.750 1.4319 0.05196 0.04112 -0.0658 0.2440 1.0000
11.000 1.4451 0.05322 0.04247 -0.0645 0.2395 1.0000
11.250 1.4454 0.05504 0.04443 -0.0624 0.2345 1.0000
11.500 1.4269 0.05848 0.04819 -0.0596 0.2303 1.0000
11.750 1.4302 0.05972 0.04950 -0.0579 0.2239 1.0000
12.000 1.4256 0.06192 0.05180 -0.0562 0.2186 1.0000
12.250 1.3962 0.06751 0.05773 -0.0549 0.2161 1.0000
12.500 1.3540 0.07572 0.06625 -0.0550 0.2155 1.0000
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Polar data table (+)
Polar graphs
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