GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 492 AIRFOIL (goe492-il) Reynolds number: 200,000 Max Cl/Cd: 78.61 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe492-il-200000-n5.txt Download as CSV file: xf-goe492-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 492 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4003 0.08680 0.08344 -0.0309 1.0000 0.0124
-7.500 -0.4114 0.08406 0.08080 -0.0297 1.0000 0.0117
-7.250 -0.4266 0.08064 0.07749 -0.0292 1.0000 0.0106
-7.000 -0.4309 0.07788 0.07479 -0.0291 1.0000 0.0103
-6.750 -0.4206 0.07466 0.07158 -0.0320 0.9985 0.0100
-6.500 -0.3971 0.06866 0.06552 -0.0403 0.9935 0.0095
-6.250 -0.3681 0.06158 0.05837 -0.0509 0.9881 0.0094
-6.000 -0.3361 0.05458 0.05126 -0.0608 0.9823 0.0097
-5.750 -0.2985 0.04562 0.04209 -0.0720 0.9779 0.0100
-5.500 -0.2672 0.03548 0.03147 -0.0806 0.9712 0.0104
-5.250 -0.2331 0.02778 0.02302 -0.0862 0.9677 0.0105
-5.000 -0.2054 0.02293 0.01741 -0.0879 0.9630 0.0107
-4.750 -0.1755 0.01944 0.01323 -0.0891 0.9595 0.0114
-4.500 -0.1433 0.01728 0.01058 -0.0902 0.9570 0.0126
-4.250 -0.1096 0.01617 0.00916 -0.0916 0.9551 0.0159
-4.000 -0.0818 0.01480 0.00750 -0.0915 0.9506 0.0183
-3.750 -0.0514 0.01400 0.00661 -0.0921 0.9469 0.0250
-3.500 -0.0183 0.01354 0.00602 -0.0932 0.9440 0.0369
-3.250 0.0156 0.01327 0.00560 -0.0946 0.9416 0.0484
-3.000 0.0433 0.01282 0.00511 -0.0948 0.9365 0.0570
-2.750 0.0738 0.01242 0.00459 -0.0954 0.9321 0.0613
-2.500 0.1066 0.01201 0.00405 -0.0964 0.9289 0.0654
-2.250 0.1360 0.01169 0.00369 -0.0968 0.9239 0.0721
-2.000 0.1656 0.01139 0.00338 -0.0972 0.9186 0.0859
-1.750 0.1972 0.01080 0.00312 -0.0983 0.9148 0.1725
-1.500 0.2245 0.01061 0.00309 -0.0982 0.9081 0.2520
-1.250 0.2551 0.01048 0.00298 -0.0988 0.9027 0.2893
-1.000 0.2842 0.01033 0.00286 -0.0990 0.8963 0.3142
-0.750 0.3127 0.01011 0.00273 -0.0992 0.8892 0.3437
-0.500 0.3405 0.00983 0.00263 -0.0992 0.8816 0.3854
-0.250 0.3641 0.00898 0.00266 -0.0984 0.8737 0.6494
0.000 0.4057 0.00827 0.00257 -0.1008 0.8667 1.0000
0.250 0.4347 0.00826 0.00249 -0.1009 0.8580 1.0000
0.500 0.4617 0.00828 0.00245 -0.1006 0.8469 1.0000
0.750 0.4886 0.00830 0.00242 -0.1002 0.8345 1.0000
1.000 0.5155 0.00832 0.00242 -0.0998 0.8210 1.0000
1.250 0.5423 0.00835 0.00241 -0.0994 0.8061 1.0000
1.500 0.5691 0.00840 0.00242 -0.0990 0.7901 1.0000
1.750 0.5956 0.00847 0.00250 -0.0986 0.7745 1.0000
2.000 0.6221 0.00855 0.00259 -0.0982 0.7588 1.0000
2.250 0.6485 0.00865 0.00270 -0.0978 0.7425 1.0000
2.500 0.6748 0.00876 0.00283 -0.0973 0.7249 1.0000
2.750 0.7002 0.00892 0.00299 -0.0966 0.6990 1.0000
3.000 0.7232 0.00920 0.00309 -0.0952 0.6527 1.0000
3.250 0.7412 0.00979 0.00327 -0.0929 0.5669 1.0000
3.500 0.7511 0.01102 0.00361 -0.0894 0.3860 1.0000
3.750 0.7517 0.01396 0.00482 -0.0856 0.0478 1.0000
4.000 0.7726 0.01480 0.00561 -0.0842 0.0220 1.0000
4.250 0.7936 0.01565 0.00659 -0.0828 0.0173 1.0000
4.500 0.8147 0.01645 0.00755 -0.0815 0.0153 1.0000
4.750 0.8352 0.01731 0.00851 -0.0802 0.0126 1.0000
5.000 0.8539 0.01847 0.00977 -0.0785 0.0116 1.0000
5.250 0.8724 0.01989 0.01130 -0.0767 0.0108 1.0000
5.500 0.8925 0.02172 0.01321 -0.0752 0.0102 1.0000
5.750 0.9155 0.02438 0.01606 -0.0741 0.0091 1.0000
6.000 0.9400 0.02567 0.01757 -0.0731 0.0081 1.0000
6.250 0.9645 0.02803 0.02022 -0.0721 0.0079 1.0000
6.500 0.9874 0.03072 0.02326 -0.0707 0.0078 1.0000
6.750 1.0076 0.03380 0.02674 -0.0690 0.0079 1.0000
7.000 1.0247 0.03717 0.03051 -0.0669 0.0080 1.0000
7.250 1.0384 0.04081 0.03462 -0.0646 0.0082 1.0000
7.500 1.0480 0.04477 0.03897 -0.0620 0.0085 1.0000
7.750 1.0530 0.04910 0.04366 -0.0593 0.0088 1.0000
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Polar data table (+)
Polar graphs
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