GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 57 AIRFOIL (goe57-il) Reynolds number: 500,000 Max Cl/Cd: 93.02 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe57-il-500000.txt Download as CSV file: xf-goe57-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 57 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3163 0.10184 0.09962 -0.0268 1.0000 0.0200
-8.250 -0.3195 0.09974 0.09758 -0.0270 1.0000 0.0201
-8.000 -0.3264 0.09799 0.09588 -0.0258 1.0000 0.0201
-7.250 -0.3199 0.08843 0.08642 -0.0236 0.9977 0.0207
-7.000 -0.2968 0.08480 0.08278 -0.0280 0.9952 0.0212
-6.750 -0.2713 0.08117 0.07913 -0.0337 0.9915 0.0223
-6.500 -0.2413 0.07688 0.07482 -0.0415 0.9869 0.0243
-6.250 -0.1865 0.07118 0.06903 -0.0606 0.9808 0.0256
-6.000 -0.1504 0.06622 0.06401 -0.0693 0.9756 0.0257
-2.000 0.3312 0.01987 0.01551 -0.1145 0.8304 0.0486
-1.750 0.3612 0.01917 0.01456 -0.1142 0.8200 0.0537
-1.500 0.3905 0.01906 0.01419 -0.1138 0.8087 0.0549
-1.250 0.4179 0.01555 0.01038 -0.1147 0.7973 0.0576
-1.000 0.4448 0.01476 0.00951 -0.1146 0.7838 0.0594
-0.750 0.4744 0.01303 0.00743 -0.1142 0.7702 0.0511
-0.500 0.5030 0.01130 0.00528 -0.1138 0.7538 0.0464
-0.250 0.5300 0.01061 0.00440 -0.1134 0.7316 0.0461
0.000 0.5566 0.01007 0.00369 -0.1128 0.7082 0.0460
0.250 0.5829 0.00977 0.00324 -0.1123 0.6815 0.0469
0.500 0.6087 0.00962 0.00293 -0.1117 0.6533 0.0485
0.750 0.6344 0.00955 0.00270 -0.1111 0.6238 0.0501
1.000 0.6604 0.00949 0.00253 -0.1107 0.5972 0.0518
1.250 0.6865 0.00950 0.00241 -0.1102 0.5694 0.0537
1.500 0.7123 0.00946 0.00225 -0.1097 0.5366 0.0574
1.750 0.7376 0.00957 0.00220 -0.1092 0.4944 0.0630
2.000 0.7622 0.00983 0.00223 -0.1086 0.4478 0.0687
2.250 0.7871 0.01005 0.00229 -0.1080 0.4064 0.0840
2.500 0.8124 0.01007 0.00248 -0.1078 0.3693 0.2285
2.750 0.8335 0.00896 0.00273 -0.1067 0.3333 1.0000
3.000 0.8580 0.00941 0.00291 -0.1061 0.2899 1.0000
3.250 0.8820 0.00992 0.00314 -0.1055 0.2436 1.0000
3.500 0.9069 0.01031 0.00336 -0.1050 0.2193 1.0000
3.750 0.9324 0.01063 0.00357 -0.1046 0.2075 1.0000
4.000 0.9576 0.01096 0.00379 -0.1042 0.1959 1.0000
4.250 0.9827 0.01129 0.00405 -0.1037 0.1871 1.0000
4.500 1.0086 0.01153 0.00427 -0.1034 0.1829 1.0000
4.750 1.0344 0.01176 0.00449 -0.1030 0.1787 1.0000
5.000 1.0592 0.01211 0.00477 -0.1026 0.1723 1.0000
5.250 1.0852 0.01229 0.00498 -0.1023 0.1658 1.0000
5.500 1.1100 0.01263 0.00526 -0.1018 0.1577 1.0000
5.750 1.1361 0.01279 0.00541 -0.1015 0.1480 1.0000
6.000 1.1614 0.01306 0.00559 -0.1011 0.1314 1.0000
6.250 1.1779 0.01440 0.00645 -0.0995 0.0448 1.0000
6.500 1.1994 0.01516 0.00710 -0.0985 0.0206 1.0000
6.750 1.2227 0.01567 0.00767 -0.0977 0.0188 1.0000
7.000 1.2454 0.01624 0.00833 -0.0967 0.0172 1.0000
7.250 1.2669 0.01695 0.00915 -0.0957 0.0159 1.0000
7.500 1.2886 0.01760 0.00990 -0.0946 0.0154 1.0000
7.750 1.3092 0.01835 0.01074 -0.0935 0.0149 1.0000
8.000 1.3286 0.01920 0.01168 -0.0921 0.0144 1.0000
8.250 1.3466 0.02014 0.01271 -0.0906 0.0140 1.0000
8.500 1.3628 0.02119 0.01385 -0.0888 0.0136 1.0000
8.750 1.3774 0.02232 0.01509 -0.0867 0.0133 1.0000
9.000 1.3900 0.02355 0.01640 -0.0845 0.0130 1.0000
9.250 1.3996 0.02494 0.01786 -0.0819 0.0125 1.0000
9.500 1.4033 0.02666 0.01963 -0.0785 0.0121 1.0000
9.750 1.4058 0.02851 0.02153 -0.0750 0.0118 1.0000
10.000 1.4123 0.03026 0.02334 -0.0721 0.0118 1.0000
10.250 1.4219 0.03201 0.02514 -0.0698 0.0117 1.0000
10.500 1.4342 0.03381 0.02702 -0.0679 0.0117 1.0000
10.750 1.4478 0.03551 0.02878 -0.0661 0.0118 1.0000
11.000 1.4595 0.03700 0.03037 -0.0642 0.0119 1.0000
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Polar data table (+)
Polar graphs
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