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GOE 572 AIRFOIL (goe572-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 572 AIRFOIL (goe572-il)
Reynolds number: 200,000
Max Cl/Cd: 54.78 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe572-il-200000-n5.txt
Download as CSV file: xf-goe572-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 572 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.2423   0.09925   0.09362  -0.1348   0.6030   0.0245
 -11.250   0.2474   0.09650   0.09084  -0.1353   0.5957   0.0228
 -11.000   0.2512   0.09378   0.08809  -0.1360   0.5903   0.0225
 -10.750   0.2551   0.09134   0.08564  -0.1368   0.5845   0.0245
 -10.500   0.2578   0.08857   0.08286  -0.1375   0.5793   0.0245
 -10.250   0.2616   0.08605   0.08030  -0.1379   0.5735   0.0239
 -10.000   0.2641   0.08335   0.07760  -0.1384   0.5688   0.0234
  -9.750   0.2652   0.08057   0.07482  -0.1389   0.5638   0.0234
  -9.500   0.2654   0.07780   0.07205  -0.1393   0.5595   0.0233
  -9.250   0.2641   0.07495   0.06919  -0.1398   0.5557   0.0235
  -9.000   0.2623   0.07209   0.06636  -0.1402   0.5512   0.0230
  -8.750   0.2550   0.06872   0.06303  -0.1410   0.5477   0.0245
  -8.500   0.2497   0.06579   0.06012  -0.1413   0.5440   0.0244
  -8.250   0.2383   0.06245   0.05681  -0.1418   0.5409   0.0245
  -8.000   0.2220   0.05916   0.05353  -0.1416   0.5380   0.0246
  -7.750   0.1935   0.05523   0.04964  -0.1396   0.5359   0.0250
  -7.500   0.1793   0.05174   0.04612  -0.1381   0.5328   0.0249
  -7.250   0.1502   0.04558   0.03981  -0.1353   0.5311   0.0252
  -7.000   0.1143   0.03813   0.03198  -0.1296   0.5298   0.0256
  -6.750   0.1223   0.03720   0.03093  -0.1272   0.5254   0.0260
  -6.500   0.1331   0.03647   0.03007  -0.1250   0.5217   0.0265
  -6.250   0.1411   0.03512   0.02860  -0.1224   0.5173   0.0273
  -6.000   0.1391   0.03219   0.02532  -0.1180   0.5140   0.0289
  -5.750   0.1241   0.02745   0.01968  -0.1107   0.5116   0.0307
  -5.500   0.1389   0.02670   0.01882  -0.1086   0.5076   0.0314
  -5.250   0.1559   0.02623   0.01823  -0.1067   0.5038   0.0322
  -5.000   0.1731   0.02575   0.01766  -0.1048   0.4992   0.0335
  -4.750   0.1874   0.02466   0.01627  -0.1022   0.4952   0.0350
  -4.500   0.2021   0.02345   0.01462  -0.0995   0.4915   0.0366
  -4.250   0.2204   0.02276   0.01374  -0.0977   0.4880   0.0379
  -4.000   0.2400   0.02240   0.01336  -0.0962   0.4838   0.0392
  -3.750   0.2597   0.02189   0.01271  -0.0946   0.4798   0.0404
  -3.500   0.2798   0.02130   0.01194  -0.0929   0.4758   0.0416
  -3.250   0.3010   0.02085   0.01126  -0.0915   0.4724   0.0432
  -3.000   0.3219   0.02048   0.01072  -0.0900   0.4679   0.0446
  -2.750   0.3435   0.01991   0.01013  -0.0889   0.4641   0.0459
  -2.500   0.3644   0.01956   0.00972  -0.0875   0.4601   0.0471
  -2.250   0.3857   0.01930   0.00936  -0.0862   0.4568   0.0484
  -2.000   0.4069   0.01907   0.00908  -0.0849   0.4531   0.0502
  -1.750   0.4272   0.01885   0.00882  -0.0834   0.4487   0.0522
  -1.500   0.4472   0.01867   0.00854  -0.0818   0.4447   0.0536
  -1.250   0.4663   0.01839   0.00822  -0.0801   0.4413   0.0553
  -1.000   0.4856   0.01823   0.00804  -0.0784   0.4381   0.0574
  -0.750   0.5039   0.01813   0.00795  -0.0766   0.4342   0.0606
  -0.500   0.5216   0.01804   0.00782  -0.0746   0.4305   0.0633
  -0.250   0.5388   0.01795   0.00768  -0.0725   0.4271   0.0667
   0.000   0.5561   0.01789   0.00756  -0.0705   0.4237   0.0721
   0.250   0.5739   0.01787   0.00752  -0.0685   0.4199   0.0782
   0.500   0.5916   0.01784   0.00753  -0.0666   0.4161   0.0881
   0.750   0.6096   0.01783   0.00755  -0.0648   0.4127   0.1089
   1.000   0.6270   0.01775   0.00761  -0.0630   0.4093   0.1603
   1.250   0.6445   0.01739   0.00779  -0.0615   0.4061   0.3421
   1.750   0.9618   0.01777   0.00915  -0.1187   0.3903   1.0000
   2.000   0.9774   0.01796   0.00931  -0.1165   0.3863   1.0000
   2.250   0.9914   0.01816   0.00946  -0.1140   0.3829   1.0000
   2.500   1.0043   0.01837   0.00959  -0.1113   0.3797   1.0000
   2.750   1.0170   0.01861   0.00973  -0.1087   0.3767   1.0000
   3.000   1.0313   0.01884   0.00994  -0.1063   0.3735   1.0000
   3.250   1.0457   0.01909   0.01017  -0.1041   0.3702   1.0000
   3.500   1.0596   0.01935   0.01040  -0.1017   0.3670   1.0000
   3.750   1.0732   0.01965   0.01063  -0.0994   0.3641   1.0000
   4.000   1.0861   0.01998   0.01088  -0.0971   0.3611   1.0000
   4.250   1.1012   0.02030   0.01120  -0.0951   0.3582   1.0000
   4.500   1.1156   0.02064   0.01155  -0.0931   0.3550   1.0000
   4.750   1.1296   0.02101   0.01190  -0.0911   0.3521   1.0000
   5.000   1.1433   0.02141   0.01227  -0.0891   0.3494   1.0000
   5.250   1.1565   0.02184   0.01265  -0.0870   0.3468   1.0000
   5.500   1.1707   0.02229   0.01309  -0.0852   0.3445   1.0000
   5.750   1.1845   0.02276   0.01359  -0.0835   0.3416   1.0000
   6.000   1.1979   0.02327   0.01411  -0.0817   0.3388   1.0000
   6.250   1.2107   0.02381   0.01466  -0.0799   0.3362   1.0000
   6.500   1.2233   0.02439   0.01523  -0.0781   0.3338   1.0000
   6.750   1.2357   0.02501   0.01581  -0.0764   0.3315   1.0000
   7.000   1.2482   0.02567   0.01649  -0.0749   0.3291   1.0000
   7.250   1.2595   0.02640   0.01728  -0.0732   0.3261   1.0000
   7.500   1.2708   0.02717   0.01808  -0.0717   0.3235   1.0000
   7.750   1.2814   0.02798   0.01891  -0.0701   0.3209   1.0000
   8.000   1.2921   0.02883   0.01976  -0.0686   0.3185   1.0000
   8.250   1.3033   0.02969   0.02059  -0.0673   0.3163   1.0000
   8.500   1.3135   0.03066   0.02162  -0.0659   0.3141   1.0000
   8.750   1.3225   0.03173   0.02277  -0.0646   0.3116   1.0000
   9.000   1.3315   0.03284   0.02394  -0.0634   0.3094   1.0000
   9.250   1.3398   0.03402   0.02519  -0.0621   0.3070   1.0000
   9.500   1.3490   0.03517   0.02636  -0.0610   0.3050   1.0000
   9.750   1.3585   0.03632   0.02751  -0.0600   0.3029   1.0000
  10.000   1.3700   0.03734   0.02851  -0.0591   0.3011   1.0000
  10.250   1.3761   0.03884   0.03012  -0.0580   0.2992   1.0000
  10.500   1.3806   0.04052   0.03190  -0.0570   0.2969   1.0000
  10.750   1.3858   0.04216   0.03365  -0.0560   0.2950   1.0000
  11.000   1.3888   0.04403   0.03559  -0.0551   0.2922   1.0000
  11.250   1.3916   0.04588   0.03745  -0.0542   0.2887   1.0000
  11.500   1.3980   0.04744   0.03897  -0.0535   0.2856   1.0000
  11.750   1.3912   0.05046   0.04217  -0.0526   0.2822   1.0000
  12.000   1.3836   0.05362   0.04546  -0.0518   0.2777   1.0000
  12.250   1.3835   0.05604   0.04790  -0.0512   0.2743   1.0000
  12.500   1.3880   0.05794   0.04977  -0.0507   0.2710   1.0000
  12.750   1.3825   0.06116   0.05315  -0.0503   0.2686   1.0000
  13.000   1.3748   0.06467   0.05680  -0.0499   0.2657   1.0000
  13.250   1.3675   0.06818   0.06041  -0.0495   0.2624   1.0000
  13.500   1.3653   0.07107   0.06333  -0.0493   0.2587   1.0000
  13.750   1.3627   0.07405   0.06634  -0.0491   0.2548   1.0000
  14.000   1.3523   0.07814   0.07059  -0.0490   0.2526   1.0000
  14.250   1.3315   0.08363   0.07623  -0.0489   0.2482   1.0000
  14.500   1.3240   0.08744   0.08010  -0.0490   0.2445   1.0000
  14.750   1.3285   0.08964   0.08227  -0.0490   0.2408   1.0000
  15.000   1.2988   0.09662   0.08947  -0.0493   0.2374   1.0000
  15.250   1.2712   0.10342   0.09644  -0.0497   0.2343   1.0000
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