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GOE 265 AIRFOIL (goe265-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 265 AIRFOIL (goe265-il)
Reynolds number: 500,000
Max Cl/Cd: 111.23 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe265-il-500000.txt
Download as CSV file: xf-goe265-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 265 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  -0.2490   0.10202   0.09994  -0.0191   1.0000   0.0218
  -8.250  -0.2454   0.09933   0.09730  -0.0220   1.0000   0.0218
  -8.000  -0.2388   0.09582   0.09383  -0.0235   0.9967   0.0220
  -7.750  -0.2162   0.09179   0.08978  -0.0255   0.9652   0.0223
  -7.500  -0.1978   0.08877   0.08668  -0.0281   0.9226   0.0227
  -7.250  -0.1892   0.08653   0.08433  -0.0287   0.8870   0.0232
  -7.000  -0.1783   0.08405   0.08173  -0.0303   0.8587   0.0239
  -6.750  -0.1642   0.08111   0.07870  -0.0333   0.8327   0.0251
  -6.500  -0.1340   0.07638   0.07382  -0.0475   0.8088   0.0262
  -6.250  -0.1251   0.07302   0.07039  -0.0455   0.7893   0.0265
  -6.000  -0.1098   0.07071   0.06798  -0.0460   0.7704   0.0269
  -5.750  -0.0905   0.06827   0.06544  -0.0483   0.7529   0.0276
  -5.500  -0.0681   0.06550   0.06257  -0.0518   0.7370   0.0288
  -5.250  -0.0156   0.05978   0.05665  -0.0680   0.7242   0.0312
  -5.000  -0.0027   0.05657   0.05339  -0.0675   0.7125   0.0317
  -4.750   0.0163   0.05489   0.05164  -0.0676   0.7012   0.0325
  -4.500   0.0429   0.05257   0.04926  -0.0705   0.6906   0.0341
  -4.250   0.0989   0.04614   0.04257  -0.0840   0.6820   0.0375
  -4.000   0.1183   0.04446   0.04086  -0.0838   0.6717   0.0381
  -3.750   0.1421   0.04301   0.03935  -0.0846   0.6620   0.0394
  -3.500   0.1994   0.03901   0.03504  -0.0938   0.6528   0.0440
  -3.250   0.2217   0.03570   0.03168  -0.0954   0.6439   0.0451
  -3.000   0.2461   0.03455   0.03045  -0.0957   0.6348   0.0462
  -2.750   0.2764   0.03295   0.02876  -0.0974   0.6253   0.0493
  -2.500   0.3437   0.01653   0.01095  -0.1097   0.6211   0.0438
  -2.250   0.3744   0.01335   0.00712  -0.1110   0.6130   0.0454
  -2.000   0.4025   0.01316   0.00685  -0.1108   0.6041   0.0468
  -1.750   0.4312   0.01257   0.00611  -0.1108   0.5956   0.0483
  -1.500   0.4597   0.01202   0.00534  -0.1107   0.5871   0.0499
  -1.250   0.4883   0.01157   0.00473  -0.1106   0.5783   0.0515
  -1.000   0.5165   0.01106   0.00404  -0.1105   0.5704   0.0539
  -0.750   0.5449   0.01094   0.00393  -0.1104   0.5622   0.0564
  -0.500   0.5729   0.01083   0.00372  -0.1102   0.5543   0.0594
  -0.250   0.6013   0.01063   0.00344  -0.1100   0.5458   0.0625
   0.000   0.6292   0.01053   0.00332  -0.1098   0.5378   0.0671
   0.250   0.6574   0.01056   0.00332  -0.1096   0.5295   0.0722
   0.500   0.6853   0.01049   0.00321  -0.1095   0.5214   0.0781
   0.750   0.7133   0.01053   0.00323  -0.1093   0.5117   0.0836
   1.000   0.7411   0.01045   0.00310  -0.1091   0.5020   0.0891
   1.250   0.7688   0.01053   0.00316  -0.1089   0.4920   0.0946
   1.500   0.7967   0.01059   0.00318  -0.1087   0.4819   0.0994
   1.750   0.8243   0.01051   0.00309  -0.1085   0.4720   0.1052
   2.000   0.8519   0.01057   0.00312  -0.1083   0.4612   0.1108
   2.250   0.8796   0.01062   0.00313  -0.1082   0.4508   0.1146
   2.500   0.9070   0.01058   0.00309  -0.1080   0.4403   0.1208
   2.750   0.9343   0.01066   0.00313  -0.1078   0.4289   0.1262
   3.000   0.9617   0.01071   0.00315  -0.1076   0.4172   0.1311
   3.250   0.9889   0.01077   0.00322  -0.1074   0.4059   0.1384
   3.500   1.0159   0.01091   0.00331  -0.1072   0.3953   0.1453
   3.750   1.0430   0.01099   0.00341  -0.1070   0.3852   0.1546
   4.000   1.0701   0.01110   0.00353  -0.1068   0.3763   0.1665
   4.250   1.0967   0.01126   0.00369  -0.1066   0.3670   0.1865
   4.500   1.1238   0.01122   0.00392  -0.1066   0.3584   0.3155
   4.750   1.1475   0.01041   0.00413  -0.1059   0.3509   1.0000
   5.000   1.1745   0.01058   0.00428  -0.1057   0.3441   1.0000
   5.250   1.2007   0.01084   0.00449  -0.1054   0.3374   1.0000
   5.500   1.2273   0.01105   0.00469  -0.1051   0.3315   1.0000
   5.750   1.2536   0.01127   0.00489  -0.1049   0.3257   1.0000
   6.000   1.2793   0.01158   0.00515  -0.1045   0.3202   1.0000
   6.250   1.3059   0.01175   0.00536  -0.1043   0.3148   1.0000
   6.500   1.3319   0.01199   0.00560  -0.1040   0.3092   1.0000
   6.750   1.3573   0.01230   0.00589  -0.1036   0.3040   1.0000
   7.000   1.3836   0.01247   0.00612  -0.1034   0.2987   1.0000
   7.250   1.4091   0.01274   0.00638  -0.1031   0.2929   1.0000
   7.500   1.4343   0.01302   0.00667  -0.1027   0.2876   1.0000
   7.750   1.4602   0.01323   0.00694  -0.1024   0.2815   1.0000
   8.000   1.4845   0.01357   0.00725  -0.1020   0.2738   1.0000
   8.250   1.5101   0.01377   0.00750  -0.1017   0.2647   1.0000
   8.500   1.5345   0.01408   0.00782  -0.1012   0.2547   1.0000
   8.750   1.5582   0.01445   0.00817  -0.1007   0.2427   1.0000
   9.000   1.5815   0.01485   0.00855  -0.1002   0.2279   1.0000
   9.250   1.6032   0.01540   0.00901  -0.0995   0.2052   1.0000
   9.500   1.6208   0.01633   0.00974  -0.0983   0.1712   1.0000
   9.750   1.6368   0.01738   0.01061  -0.0969   0.1461   1.0000
  10.000   1.6543   0.01822   0.01139  -0.0957   0.1352   1.0000
  10.250   1.6730   0.01889   0.01209  -0.0946   0.1291   1.0000
  10.500   1.6899   0.01967   0.01289  -0.0933   0.1234   1.0000
  10.750   1.7069   0.02039   0.01365  -0.0920   0.1176   1.0000
  11.000   1.7227   0.02115   0.01444  -0.0905   0.1117   1.0000
  11.250   1.7358   0.02203   0.01534  -0.0888   0.1053   1.0000
  11.500   1.7490   0.02273   0.01609  -0.0869   0.0977   1.0000
  11.750   1.7585   0.02367   0.01702  -0.0847   0.0848   1.0000
  12.000   1.7508   0.02590   0.01898  -0.0812   0.0539   1.0000
  12.250   1.7350   0.02913   0.02209  -0.0780   0.0321   1.0000
  12.500   1.7255   0.03230   0.02525  -0.0761   0.0234   1.0000
  12.750   1.7226   0.03512   0.02816  -0.0751   0.0208   1.0000
  13.000   1.7179   0.03836   0.03149  -0.0745   0.0191   1.0000
  13.250   1.7160   0.04142   0.03468  -0.0741   0.0182   1.0000
  13.500   1.7122   0.04477   0.03816  -0.0738   0.0175   1.0000
  13.750   1.7057   0.04853   0.04204  -0.0738   0.0168   1.0000
  14.000   1.6968   0.05267   0.04632  -0.0738   0.0164   1.0000
  14.250   1.6852   0.05723   0.05100  -0.0741   0.0159   1.0000
  14.500   1.6710   0.06224   0.05614  -0.0746   0.0156   1.0000
  14.750   1.6553   0.06758   0.06162  -0.0753   0.0153   1.0000
  15.000   1.6385   0.07328   0.06745  -0.0762   0.0150   1.0000
  15.250   1.6282   0.07818   0.07248  -0.0771   0.0149   1.0000
  15.500   1.6164   0.08337   0.07780  -0.0781   0.0147   1.0000
  15.750   1.6040   0.08877   0.08333  -0.0793   0.0145   1.0000
  16.000   1.5916   0.09427   0.08895  -0.0806   0.0143   1.0000
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