GOE 458 AIRFOIL (goe458-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 458 AIRFOIL (goe458-il) Reynolds number: 500,000 Max Cl/Cd: 117.84 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe458-il-500000.txt Download as CSV file: xf-goe458-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 458 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3093 0.10206 0.09992 -0.0320 1.0000 0.0099
-8.500 -0.3136 0.10018 0.09807 -0.0305 1.0000 0.0098
-8.250 -0.3165 0.09807 0.09601 -0.0296 0.9996 0.0103
-8.000 -0.2994 0.09391 0.09184 -0.0344 0.9973 0.0109
-7.750 -0.2810 0.08967 0.08761 -0.0399 0.9943 0.0118
-7.500 -0.2626 0.08574 0.08368 -0.0462 0.9891 0.0125
-7.250 -0.2391 0.08170 0.07965 -0.0535 0.9843 0.0129
-7.000 -0.2169 0.07710 0.07504 -0.0602 0.9787 0.0130
-6.750 -0.1917 0.07212 0.07005 -0.0681 0.9737 0.0131
-6.500 -0.1677 0.06387 0.06179 -0.0793 0.9703 0.0136
-6.250 -0.1472 0.06030 0.05821 -0.0835 0.9651 0.0146
-6.000 -0.1186 0.05670 0.05455 -0.0895 0.9608 0.0158
-5.750 -0.0835 0.05172 0.04951 -0.0984 0.9570 0.0167
-5.500 -0.0537 0.04700 0.04470 -0.1052 0.9491 0.0178
-5.250 -0.0179 0.04155 0.03912 -0.1129 0.9432 0.0191
-5.000 0.0142 0.03642 0.03381 -0.1178 0.9340 0.0209
-4.750 0.0484 0.03142 0.02844 -0.1220 0.9271 0.0218
-4.500 0.0666 0.02377 0.02019 -0.1248 0.9175 0.0231
-4.250 0.0892 0.02152 0.01780 -0.1251 0.9098 0.0248
-4.000 0.1148 0.01974 0.01578 -0.1253 0.9030 0.0273
-3.750 0.1405 0.01821 0.01391 -0.1249 0.8949 0.0309
-3.500 0.1679 0.01307 0.00781 -0.1234 0.8884 0.0161
-3.250 0.1934 0.01185 0.00635 -0.1226 0.8802 0.0168
-3.000 0.2206 0.01112 0.00545 -0.1223 0.8735 0.0184
-2.750 0.2467 0.01042 0.00463 -0.1217 0.8651 0.0197
-2.500 0.2731 0.00967 0.00373 -0.1211 0.8572 0.0201
-2.250 0.2998 0.00917 0.00311 -0.1206 0.8489 0.0214
-2.000 0.3260 0.00864 0.00242 -0.1200 0.8400 0.0248
-1.750 0.3530 0.00833 0.00204 -0.1196 0.8317 0.0371
-1.500 0.3788 0.00790 0.00190 -0.1192 0.8221 0.1521
-1.250 0.4053 0.00783 0.00186 -0.1189 0.8119 0.1752
-1.000 0.4320 0.00779 0.00178 -0.1186 0.8017 0.1920
-0.750 0.4586 0.00774 0.00170 -0.1183 0.7913 0.2091
-0.500 0.4850 0.00767 0.00164 -0.1180 0.7800 0.2280
-0.250 0.5111 0.00759 0.00159 -0.1176 0.7671 0.2544
0.000 0.5369 0.00749 0.00155 -0.1171 0.7526 0.2997
0.250 0.5620 0.00732 0.00153 -0.1166 0.7364 0.3777
0.500 0.6000 0.00600 0.00158 -0.1191 0.7200 1.0000
0.750 0.6253 0.00610 0.00157 -0.1185 0.7040 1.0000
1.000 0.6507 0.00622 0.00157 -0.1179 0.6892 1.0000
1.250 0.6762 0.00635 0.00160 -0.1173 0.6751 1.0000
1.500 0.7015 0.00649 0.00164 -0.1168 0.6612 1.0000
1.750 0.7267 0.00663 0.00170 -0.1162 0.6469 1.0000
2.000 0.7521 0.00678 0.00177 -0.1157 0.6340 1.0000
2.250 0.7779 0.00691 0.00185 -0.1153 0.6236 1.0000
2.500 0.8036 0.00706 0.00197 -0.1149 0.6147 1.0000
2.750 0.8296 0.00719 0.00208 -0.1145 0.6055 1.0000
3.000 0.8554 0.00732 0.00220 -0.1141 0.5963 1.0000
3.250 0.8796 0.00749 0.00231 -0.1133 0.5773 1.0000
3.500 0.9038 0.00767 0.00243 -0.1126 0.5567 1.0000
3.750 0.9270 0.00789 0.00258 -0.1117 0.5283 1.0000
4.000 0.9503 0.00812 0.00274 -0.1108 0.4997 1.0000
4.250 0.9694 0.00863 0.00295 -0.1092 0.4313 1.0000
4.500 0.9737 0.01051 0.00376 -0.1054 0.2388 1.0000
5.000 0.9972 0.01337 0.00551 -0.1001 0.0205 1.0000
5.250 1.0194 0.01383 0.00612 -0.0990 0.0184 1.0000
5.500 1.0403 0.01440 0.00679 -0.0977 0.0159 1.0000
5.750 1.0591 0.01515 0.00764 -0.0961 0.0143 1.0000
6.000 1.0745 0.01620 0.00881 -0.0938 0.0132 1.0000
6.250 1.0847 0.01763 0.01038 -0.0907 0.0126 1.0000
6.500 1.0959 0.01900 0.01182 -0.0877 0.0125 1.0000
6.750 1.1100 0.02022 0.01312 -0.0853 0.0126 1.0000
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Polar data table (+)
Polar graphs
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