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GOE 63 AIRFOIL (goe63-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 63 AIRFOIL (goe63-il)
Reynolds number: 200,000
Max Cl/Cd: 80.71 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe63-il-200000-n5.txt
Download as CSV file: xf-goe63-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 63 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1665   0.09643   0.09272  -0.0407   0.8710   0.0287
  -7.750  -0.1603   0.09456   0.09076  -0.0438   0.8488   0.0289
  -7.500  -0.1503   0.09211   0.08825  -0.0471   0.8328   0.0289
  -7.250  -0.1394   0.08860   0.08468  -0.0460   0.8213   0.0291
  -7.000  -0.1276   0.08569   0.08172  -0.0467   0.8103   0.0293
  -6.750  -0.1144   0.08297   0.07895  -0.0484   0.8004   0.0296
  -6.500  -0.0999   0.08032   0.07624  -0.0506   0.7912   0.0300
  -6.250  -0.0836   0.07762   0.07351  -0.0534   0.7821   0.0304
  -6.000  -0.0658   0.07492   0.07074  -0.0564   0.7739   0.0310
  -5.750  -0.0460   0.07214   0.06792  -0.0599   0.7659   0.0316
  -5.500  -0.0231   0.06933   0.06504  -0.0643   0.7587   0.0326
  -5.250   0.0194   0.06645   0.06198  -0.0761   0.7519   0.0335
  -5.000   0.0462   0.06328   0.05875  -0.0805   0.7450   0.0336
  -4.750   0.0606   0.06033   0.05577  -0.0800   0.7391   0.0338
  -4.500   0.0807   0.05767   0.05309  -0.0813   0.7330   0.0342
  -4.250   0.1051   0.05513   0.05050  -0.0838   0.7271   0.0347
  -4.000   0.1325   0.05264   0.04792  -0.0869   0.7220   0.0355
  -3.750   0.1626   0.05013   0.04533  -0.0905   0.7163   0.0364
  -3.500   0.1978   0.04759   0.04267  -0.0950   0.7098   0.0380
  -3.250   0.2456   0.04476   0.03953  -0.1020   0.7040   0.0391
  -3.000   0.2663   0.04240   0.03719  -0.1025   0.6969   0.0396
  -2.750   0.2936   0.04034   0.03504  -0.1042   0.6898   0.0403
  -2.500   0.3242   0.03835   0.03293  -0.1063   0.6835   0.0413
  -2.250   0.3575   0.03637   0.03083  -0.1088   0.6766   0.0428
  -2.000   0.4067   0.03473   0.02870  -0.1129   0.6701   0.0450
  -1.750   0.4339   0.03229   0.02623  -0.1143   0.6630   0.0455
  -1.500   0.4606   0.03055   0.02445  -0.1153   0.6555   0.0463
  -1.250   0.4905   0.02911   0.02288  -0.1165   0.6496   0.0476
  -1.000   0.5310   0.02800   0.02138  -0.1182   0.6437   0.0524
  -0.750   0.5576   0.02624   0.01965  -0.1192   0.6379   0.0536
  -0.500   0.5875   0.02504   0.01833  -0.1201   0.6324   0.0550
  -0.250   0.6193   0.02392   0.01707  -0.1209   0.6258   0.0571
   0.000   0.6603   0.02114   0.01366  -0.1218   0.6204   0.0391
   0.250   0.6902   0.02020   0.01259  -0.1223   0.6147   0.0381
   0.500   0.7209   0.01921   0.01146  -0.1228   0.6074   0.0376
   0.750   0.7516   0.01831   0.01030  -0.1230   0.6007   0.0379
   1.000   0.7824   0.01753   0.00924  -0.1231   0.5935   0.0389
   1.250   0.8117   0.01686   0.00842  -0.1232   0.5858   0.0388
   1.500   0.8407   0.01629   0.00772  -0.1232   0.5778   0.0388
   1.750   0.8694   0.01579   0.00712  -0.1231   0.5685   0.0390
   2.000   0.8977   0.01538   0.00668  -0.1231   0.5588   0.0395
   2.250   0.9256   0.01510   0.00634  -0.1230   0.5483   0.0403
   2.500   0.9534   0.01491   0.00617  -0.1229   0.5351   0.0424
   2.750   0.9809   0.01475   0.00595  -0.1226   0.5200   0.0445
   3.000   1.0082   0.01459   0.00575  -0.1224   0.5017   0.0456
   3.250   1.0350   0.01454   0.00565  -0.1222   0.4803   0.0473
   3.500   1.0613   0.01461   0.00562  -0.1219   0.4562   0.0496
   3.750   1.0868   0.01478   0.00565  -0.1215   0.4320   0.0538
   4.000   1.1121   0.01502   0.00577  -0.1210   0.4091   0.0604
   4.250   1.1373   0.01529   0.00595  -0.1206   0.3888   0.0730
   4.500   1.1550   0.01431   0.00627  -0.1187   0.3737   0.8740
   4.750   1.1794   0.01462   0.00644  -0.1180   0.3589   1.0000
   5.000   1.2041   0.01504   0.00672  -0.1175   0.3464   1.0000
   5.250   1.2285   0.01547   0.00704  -0.1170   0.3351   1.0000
   5.500   1.2533   0.01584   0.00735  -0.1166   0.3250   1.0000
   5.750   1.2772   0.01629   0.00772  -0.1160   0.3159   1.0000
   6.000   1.3019   0.01666   0.00806  -0.1155   0.3070   1.0000
   6.250   1.3254   0.01711   0.00845  -0.1149   0.2990   1.0000
   6.500   1.3497   0.01748   0.00884  -0.1144   0.2905   1.0000
   6.750   1.3726   0.01795   0.00926  -0.1137   0.2824   1.0000
   7.000   1.3964   0.01832   0.00966  -0.1131   0.2739   1.0000
   7.250   1.4185   0.01882   0.01011  -0.1124   0.2663   1.0000
   7.500   1.4418   0.01921   0.01056  -0.1117   0.2581   1.0000
   7.750   1.4629   0.01973   0.01105  -0.1108   0.2499   1.0000
   8.000   1.4850   0.02017   0.01152  -0.1100   0.2408   1.0000
   8.250   1.5052   0.02071   0.01207  -0.1090   0.2324   1.0000
   8.500   1.5256   0.02123   0.01262  -0.1080   0.2238   1.0000
   8.750   1.5445   0.02182   0.01321  -0.1068   0.2162   1.0000
   9.000   1.5629   0.02242   0.01385  -0.1055   0.2082   1.0000
   9.250   1.5798   0.02308   0.01453  -0.1040   0.2010   1.0000
   9.500   1.5956   0.02376   0.01524  -0.1024   0.1935   1.0000
   9.750   1.6090   0.02453   0.01603  -0.1005   0.1868   1.0000
  10.000   1.6205   0.02531   0.01684  -0.0982   0.1798   1.0000
  10.250   1.6297   0.02629   0.01783  -0.0958   0.1736   1.0000
  10.500   1.6414   0.02719   0.01880  -0.0939   0.1673   1.0000
  10.750   1.6496   0.02836   0.01998  -0.0918   0.1614   1.0000
  11.000   1.6603   0.02945   0.02114  -0.0901   0.1559   1.0000
  11.250   1.6695   0.03069   0.02245  -0.0885   0.1505   1.0000
  11.500   1.6755   0.03224   0.02400  -0.0867   0.1460   1.0000
  11.750   1.6866   0.03346   0.02535  -0.0855   0.1416   1.0000
  12.000   1.6949   0.03496   0.02692  -0.0842   0.1371   1.0000
  12.250   1.7002   0.03676   0.02876  -0.0829   0.1331   1.0000
  12.500   1.7084   0.03836   0.03048  -0.0818   0.1292   1.0000
  12.750   1.7157   0.04008   0.03229  -0.0808   0.1249   1.0000
  13.000   1.7201   0.04211   0.03438  -0.0798   0.1211   1.0000
  13.250   1.7239   0.04425   0.03659  -0.0789   0.1178   1.0000
  13.500   1.7307   0.04612   0.03860  -0.0781   0.1143   1.0000
  13.750   1.7346   0.04830   0.04090  -0.0773   0.1108   1.0000
  14.000   1.7354   0.05086   0.04353  -0.0766   0.1074   1.0000
  14.250   1.7378   0.05330   0.04608  -0.0760   0.1038   1.0000
  14.500   1.7401   0.05578   0.04868  -0.0755   0.0996   1.0000
  14.750   1.7383   0.05878   0.05176  -0.0751   0.0957   1.0000
  15.000   1.7375   0.06174   0.05484  -0.0748   0.0919   1.0000
  15.250   1.7362   0.06485   0.05806  -0.0746   0.0866   1.0000
  15.500   1.7309   0.06858   0.06186  -0.0747   0.0814   1.0000
  15.750   1.7267   0.07223   0.06562  -0.0749   0.0753   1.0000
  16.000   1.7186   0.07654   0.07001  -0.0753   0.0680   1.0000
  16.250   1.7062   0.08159   0.07511  -0.0761   0.0589   1.0000
  16.500   1.6894   0.08742   0.08097  -0.0772   0.0491   1.0000
  16.750   1.6680   0.09418   0.08775  -0.0789   0.0403   1.0000
  17.000   1.6455   0.10135   0.09497  -0.0810   0.0338   1.0000
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