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GOE 503 AIRFOIL (goe503-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 503 AIRFOIL (goe503-il)
Reynolds number: 100,000
Max Cl/Cd: 46.38 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe503-il-100000-n5.txt
Download as CSV file: xf-goe503-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 503 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0741   0.09910   0.09427  -0.0947   0.9315   0.0343
 -10.250  -0.0729   0.09389   0.08909  -0.0979   0.9228   0.0346
 -10.000  -0.0699   0.08778   0.08298  -0.1028   0.9172   0.0350
  -9.750  -0.0776   0.08156   0.07679  -0.1066   0.9064   0.0358
  -9.500  -0.0540   0.08033   0.07552  -0.1089   0.8993   0.0375
  -9.250  -0.0507   0.07558   0.07077  -0.1129   0.8896   0.0390
  -9.000  -0.0631   0.06925   0.06447  -0.1175   0.8771   0.0400
  -8.750  -0.0955   0.06169   0.05691  -0.1217   0.8617   0.0403
  -8.500  -0.1874   0.04378   0.03851  -0.1260   0.8429   0.0396
  -8.250  -0.2138   0.03669   0.03067  -0.1237   0.8304   0.0410
  -8.000  -0.1968   0.03391   0.02750  -0.1239   0.8247   0.0438
  -7.750  -0.1859   0.03272   0.02613  -0.1218   0.8144   0.0467
  -7.500  -0.1651   0.03028   0.02318  -0.1218   0.8090   0.0519
  -7.250  -0.1483   0.02992   0.02276  -0.1201   0.7994   0.0561
  -7.000  -0.1223   0.02842   0.02088  -0.1204   0.7938   0.0624
  -6.750  -0.1025   0.02815   0.02051  -0.1191   0.7852   0.0674
  -6.500  -0.0752   0.02723   0.01928  -0.1193   0.7790   0.0736
  -6.250  -0.0512   0.02723   0.01917  -0.1188   0.7713   0.0803
  -6.000  -0.0251   0.02686   0.01865  -0.1186   0.7644   0.0865
  -5.750   0.0026   0.02632   0.01789  -0.1187   0.7581   0.0919
  -5.500   0.0231   0.02532   0.01647  -0.1174   0.7502   0.0959
  -5.250   0.0547   0.02464   0.01571  -0.1182   0.7447   0.0999
  -5.000   0.0744   0.02422   0.01519  -0.1167   0.7366   0.1035
  -4.750   0.1029   0.02349   0.01417  -0.1168   0.7304   0.1079
  -4.500   0.1285   0.02290   0.01335  -0.1163   0.7237   0.1125
  -4.250   0.1521   0.02260   0.01303  -0.1156   0.7164   0.1173
  -4.000   0.1844   0.02208   0.01229  -0.1163   0.7111   0.1241
  -3.750   0.2031   0.02180   0.01194  -0.1146   0.7032   0.1291
  -3.500   0.2307   0.02155   0.01162  -0.1145   0.6970   0.1365
  -3.250   0.2558   0.02132   0.01128  -0.1139   0.6906   0.1447
  -3.000   0.2779   0.02123   0.01114  -0.1128   0.6835   0.1529
  -2.750   0.3084   0.02101   0.01080  -0.1132   0.6782   0.1621
  -2.500   0.3274   0.02099   0.01073  -0.1115   0.6709   0.1712
  -2.250   0.3528   0.02091   0.01060  -0.1110   0.6646   0.1810
  -2.000   0.3797   0.02084   0.01043  -0.1108   0.6591   0.1930
  -1.750   0.3987   0.02088   0.01042  -0.1091   0.6520   0.2046
  -1.500   0.4258   0.02078   0.01029  -0.1090   0.6467   0.2164
  -1.250   0.4479   0.02074   0.01021  -0.1079   0.6406   0.2269
  -1.000   0.4698   0.02072   0.01016  -0.1068   0.6342   0.2381
  -0.750   0.4991   0.02059   0.00998  -0.1070   0.6293   0.2503
  -0.500   0.5185   0.02064   0.01003  -0.1054   0.6229   0.2604
  -0.250   0.5426   0.02063   0.01000  -0.1047   0.6171   0.2718
   0.000   0.5735   0.02054   0.00985  -0.1053   0.6126   0.2853
   0.250   0.5902   0.02066   0.01002  -0.1033   0.6060   0.2972
   0.500   0.6149   0.02068   0.01002  -0.1027   0.6006   0.3120
   1.000   0.6595   0.02076   0.01013  -0.1008   0.5898   0.3474
   1.250   0.6824   0.02074   0.01014  -0.1000   0.5846   0.3719
   1.500   0.7097   0.02058   0.01000  -0.1000   0.5805   0.4096
   2.000   0.8918   0.02024   0.01081  -0.1262   0.5670   1.0000
   2.250   0.9101   0.02045   0.01092  -0.1245   0.5622   1.0000
   2.500   0.9216   0.02075   0.01120  -0.1215   0.5565   1.0000
   2.750   0.9408   0.02094   0.01128  -0.1200   0.5517   1.0000
   3.000   0.9630   0.02111   0.01134  -0.1190   0.5475   1.0000
   3.250   0.9705   0.02149   0.01174  -0.1154   0.5417   1.0000
   3.500   0.9876   0.02173   0.01192  -0.1135   0.5368   1.0000
   3.750   1.0124   0.02187   0.01195  -0.1130   0.5327   1.0000
   4.000   1.0188   0.02229   0.01241  -0.1092   0.5271   1.0000
   4.250   1.0326   0.02261   0.01270  -0.1067   0.5220   1.0000
   4.500   1.0554   0.02279   0.01280  -0.1059   0.5177   1.0000
   4.750   1.0680   0.02316   0.01317  -0.1033   0.5130   1.0000
   5.000   1.0744   0.02358   0.01361  -0.0996   0.5075   1.0000
   5.250   1.0933   0.02381   0.01380  -0.0981   0.5029   1.0000
   5.500   1.1154   0.02405   0.01398  -0.0972   0.4988   1.0000
   5.750   1.1120   0.02461   0.01463  -0.0918   0.4931   1.0000
   6.000   1.1262   0.02495   0.01496  -0.0896   0.4882   1.0000
   6.250   1.1533   0.02510   0.01504  -0.0896   0.4841   1.0000
   6.500   1.1505   0.02579   0.01582  -0.0846   0.4786   1.0000
   6.750   1.1599   0.02628   0.01636  -0.0817   0.4733   1.0000
   7.000   1.1834   0.02647   0.01651  -0.0812   0.4690   1.0000
   7.250   1.1874   0.02715   0.01724  -0.0776   0.4636   1.0000
   7.500   1.1923   0.02783   0.01798  -0.0743   0.4578   1.0000
   7.750   1.2140   0.02805   0.01819  -0.0735   0.4533   1.0000
   8.000   1.2176   0.02883   0.01904  -0.0702   0.4476   1.0000
   8.250   1.2209   0.02962   0.01989  -0.0669   0.4411   1.0000
   8.500   1.2463   0.02961   0.01982  -0.0666   0.4359   1.0000
   8.750   1.2342   0.03110   0.02146  -0.0617   0.4287   1.0000
   9.000   1.2470   0.03162   0.02200  -0.0599   0.4227   1.0000
   9.250   1.2561   0.03238   0.02280  -0.0578   0.4171   1.0000
   9.500   1.2524   0.03385   0.02438  -0.0545   0.4106   1.0000
   9.750   1.2711   0.03420   0.02473  -0.0536   0.4058   1.0000
  10.000   1.2684   0.03578   0.02642  -0.0507   0.3997   1.0000
  10.250   1.2704   0.03715   0.02789  -0.0484   0.3935   1.0000
  10.500   1.2941   0.03721   0.02794  -0.0480   0.3892   1.0000
  10.750   1.2764   0.04002   0.03091  -0.0445   0.3819   1.0000
  11.000   1.2870   0.04097   0.03190  -0.0432   0.3763   1.0000
  11.250   1.2960   0.04207   0.03305  -0.0418   0.3709   1.0000
  11.500   1.2837   0.04489   0.03602  -0.0394   0.3637   1.0000
  11.750   1.3041   0.04514   0.03628  -0.0388   0.3592   1.0000
  12.000   1.2905   0.04833   0.03961  -0.0367   0.3523   1.0000
  12.250   1.2937   0.05011   0.04147  -0.0354   0.3464   1.0000
  12.500   1.3228   0.04955   0.04091  -0.0352   0.3426   1.0000
  12.750   1.2881   0.05503   0.04657  -0.0329   0.3337   1.0000
  13.000   1.3075   0.05530   0.04688  -0.0323   0.3290   1.0000
  13.250   1.2907   0.05934   0.05105  -0.0309   0.3215   1.0000
  13.500   1.2986   0.06070   0.05245  -0.0302   0.3142   1.0000
  13.750   1.2871   0.06437   0.05622  -0.0292   0.3066   1.0000
  14.000   1.2925   0.06605   0.05792  -0.0286   0.2984   1.0000
  14.250   1.2775   0.07039   0.06238  -0.0280   0.2911   1.0000
  14.500   1.2855   0.07181   0.06380  -0.0275   0.2827   1.0000
  14.750   1.2646   0.07716   0.06929  -0.0272   0.2751   1.0000
  15.000   1.2730   0.07866   0.07081  -0.0269   0.2681   1.0000
  15.250   1.2588   0.08335   0.07562  -0.0269   0.2615   1.0000
  15.500   1.2571   0.08632   0.07867  -0.0268   0.2542   1.0000
  15.750   1.2460   0.09067   0.08311  -0.0271   0.2466   1.0000
  16.000   1.2421   0.09413   0.08666  -0.0272   0.2406   1.0000
  16.250   1.2415   0.09707   0.08965  -0.0274   0.2336   1.0000
  16.500   1.2278   0.10207   0.09477  -0.0281   0.2269   1.0000
  16.750   1.2361   0.10373   0.09647  -0.0281   0.2206   1.0000
  17.000   1.2137   0.11024   0.10312  -0.0294   0.2142   1.0000
  17.250   1.2259   0.11127   0.10415  -0.0294   0.2068   1.0000
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