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GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.42 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe325-il-1000000.txt
Download as CSV file: xf-goe325-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 325 (PFALZ 54) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2625   0.09246   0.09099  -0.0283   1.0000   0.0131
  -9.000  -0.2635   0.08909   0.08764  -0.0285   1.0000   0.0131
  -8.750  -0.3524   0.09856   0.09701  -0.0213   1.0000   0.0131
  -8.500  -0.3478   0.09497   0.09343  -0.0234   1.0000   0.0131
  -8.250  -0.3446   0.09157   0.09005  -0.0251   1.0000   0.0131
  -8.000  -0.3505   0.08921   0.08772  -0.0242   1.0000   0.0131
  -7.750  -0.3448   0.08396   0.08248  -0.0280   0.9967   0.0134
  -7.500  -0.3235   0.08062   0.07915  -0.0323   0.9946   0.0136
  -7.250  -0.3021   0.07710   0.07561  -0.0377   0.9906   0.0139
  -7.000  -0.2104   0.05702   0.05558  -0.0494   0.9653   0.0168
  -6.750  -0.2031   0.05243   0.05096  -0.0533   0.9570   0.0169
  -6.500  -0.1928   0.04720   0.04569  -0.0580   0.9491   0.0169
  -6.250  -0.1805   0.04198   0.04041  -0.0622   0.9423   0.0170
  -6.000  -0.1875   0.05209   0.05032  -0.0710   0.9529   0.0170
  -5.500  -0.1430   0.03662   0.03443  -0.0816   0.9389   0.0173
  -5.250  -0.1266   0.04149   0.03947  -0.0780   0.9312   0.0184
  -5.000  -0.0925   0.03809   0.03588  -0.0805   0.9241   0.0217
  -4.750  -0.0660   0.03293   0.03048  -0.0826   0.9157   0.0218
  -4.500  -0.0421   0.01942   0.01603  -0.0861   0.9082   0.0224
  -4.250  -0.0174   0.02280   0.01969  -0.0855   0.8948   0.0232
  -4.000   0.0065   0.02421   0.02117  -0.0851   0.8773   0.0248
  -3.750   0.0365   0.02365   0.02037  -0.0842   0.8552   0.0281
  -3.500   0.0611   0.01668   0.01269  -0.0851   0.8287   0.0263
  -3.250   0.0880   0.01504   0.01050  -0.0847   0.7873   0.0289
  -3.000   0.1145   0.01399   0.00908  -0.0844   0.7443   0.0288
  -2.750   0.1417   0.01282   0.00756  -0.0842   0.7090   0.0287
  -2.500   0.1688   0.01132   0.00572  -0.0842   0.6731   0.0296
  -2.250   0.1958   0.01097   0.00512  -0.0841   0.6232   0.0305
  -2.000   0.2229   0.01063   0.00453  -0.0840   0.5776   0.0309
  -1.750   0.2507   0.01026   0.00398  -0.0840   0.5528   0.0312
  -1.500   0.2786   0.00990   0.00351  -0.0839   0.5369   0.0315
  -1.250   0.3066   0.00959   0.00309  -0.0839   0.5243   0.0318
  -1.000   0.3347   0.00938   0.00281  -0.0839   0.5134   0.0326
  -0.500   0.3913   0.00898   0.00230  -0.0840   0.4943   0.0343
  -0.250   0.4195   0.00885   0.00211  -0.0840   0.4856   0.0352
   0.000   0.4479   0.00875   0.00196  -0.0841   0.4762   0.0359
   0.250   0.4763   0.00867   0.00184  -0.0841   0.4665   0.0364
   0.500   0.5045   0.00863   0.00174  -0.0842   0.4559   0.0369
   0.750   0.5329   0.00854   0.00158  -0.0843   0.4443   0.0382
   1.000   0.5612   0.00849   0.00149  -0.0843   0.4321   0.0418
   1.250   0.5894   0.00850   0.00146  -0.0844   0.4187   0.0467
   1.500   0.6176   0.00845   0.00148  -0.0844   0.4040   0.0951
   1.750   0.6390   0.00654   0.00168  -0.0837   0.3904   1.0000
   2.000   0.6669   0.00670   0.00173  -0.0837   0.3756   1.0000
   2.250   0.6947   0.00685   0.00179  -0.0837   0.3627   1.0000
   2.500   0.7224   0.00701   0.00186  -0.0837   0.3519   1.0000
   2.750   0.7501   0.00717   0.00194  -0.0837   0.3425   1.0000
   3.000   0.7780   0.00729   0.00203  -0.0837   0.3352   1.0000
   3.250   0.8056   0.00746   0.00214  -0.0837   0.3277   1.0000
   3.500   0.8335   0.00758   0.00223  -0.0837   0.3222   1.0000
   3.750   0.8611   0.00773   0.00235  -0.0837   0.3163   1.0000
   4.000   0.8887   0.00789   0.00248  -0.0837   0.3109   1.0000
   4.250   0.9165   0.00801   0.00259  -0.0838   0.3059   1.0000
   4.500   0.9436   0.00821   0.00273  -0.0837   0.2985   1.0000
   4.750   0.9714   0.00832   0.00285  -0.0837   0.2921   1.0000
   5.000   0.9985   0.00851   0.00300  -0.0837   0.2847   1.0000
   5.250   1.0260   0.00863   0.00312  -0.0837   0.2778   1.0000
   5.500   1.0531   0.00882   0.00327  -0.0837   0.2706   1.0000
   5.750   1.0804   0.00895   0.00342  -0.0837   0.2640   1.0000
   6.000   1.1072   0.00917   0.00359  -0.0836   0.2541   1.0000
   6.250   1.1341   0.00934   0.00375  -0.0836   0.2444   1.0000
   6.500   1.1606   0.00957   0.00395  -0.0835   0.2317   1.0000
   6.750   1.1862   0.00991   0.00419  -0.0833   0.2106   1.0000
   7.000   1.2018   0.01163   0.00519  -0.0818   0.0973   1.0000
   7.250   1.2175   0.01333   0.00640  -0.0803   0.0191   1.0000
   7.500   1.2421   0.01375   0.00686  -0.0799   0.0158   1.0000
   7.750   1.2660   0.01425   0.00740  -0.0794   0.0141   1.0000
   8.000   1.2886   0.01490   0.00815  -0.0786   0.0125   1.0000
   8.250   1.3124   0.01536   0.00865  -0.0781   0.0120   1.0000
   8.500   1.3355   0.01585   0.00919  -0.0775   0.0113   1.0000
   8.750   1.3579   0.01641   0.00981  -0.0768   0.0106   1.0000
   9.000   1.3791   0.01706   0.01052  -0.0759   0.0100   1.0000
   9.250   1.3972   0.01801   0.01155  -0.0746   0.0094   1.0000
   9.500   1.4106   0.01935   0.01303  -0.0726   0.0089   1.0000
   9.750   1.4305   0.01996   0.01370  -0.0716   0.0087   1.0000
  10.000   1.4482   0.02072   0.01454  -0.0703   0.0084   1.0000
  10.250   1.4640   0.02158   0.01548  -0.0687   0.0081   1.0000
  10.500   1.4783   0.02248   0.01645  -0.0669   0.0078   1.0000
  10.750   1.4914   0.02337   0.01741  -0.0650   0.0075   1.0000
  11.000   1.5011   0.02425   0.01834  -0.0625   0.0072   1.0000
  11.250   1.5090   0.02524   0.01940  -0.0600   0.0070   1.0000
  11.500   1.5134   0.02653   0.02076  -0.0573   0.0068   1.0000
  11.750   1.5120   0.02832   0.02265  -0.0542   0.0066   1.0000
  12.000   1.5049   0.03075   0.02518  -0.0512   0.0064   1.0000
  12.250   1.4890   0.03426   0.02884  -0.0482   0.0063   1.0000
  12.500   1.4834   0.03722   0.03191  -0.0467   0.0062   1.0000
  12.750   1.4877   0.03943   0.03422  -0.0461   0.0061   1.0000
  13.000   1.4891   0.04211   0.03701  -0.0458   0.0061   1.0000
  13.250   1.4895   0.04506   0.04006  -0.0458   0.0060   1.0000
  13.500   1.4883   0.04833   0.04344  -0.0460   0.0059   1.0000
  13.750   1.4859   0.05183   0.04706  -0.0464   0.0058   1.0000
  14.000   1.4826   0.05554   0.05087  -0.0469   0.0058   1.0000
  14.250   1.4787   0.05940   0.05484  -0.0475   0.0057   1.0000
  14.500   1.4741   0.06336   0.05891  -0.0482   0.0056   1.0000
  14.750   1.4690   0.06743   0.06309  -0.0489   0.0056   1.0000
  15.000   1.4636   0.07157   0.06734  -0.0497   0.0055   1.0000
  15.250   1.4577   0.07581   0.07169  -0.0506   0.0054   1.0000
  15.500   1.4514   0.08016   0.07615  -0.0516   0.0054   1.0000
  15.750   1.4447   0.08464   0.08074  -0.0527   0.0053   1.0000
  16.000   1.4380   0.08923   0.08543  -0.0540   0.0052   1.0000
  16.250   1.4310   0.09393   0.09024  -0.0555   0.0052   1.0000
  16.500   1.4236   0.09880   0.09522  -0.0570   0.0051   1.0000
  16.750   1.4161   0.10380   0.10033  -0.0588   0.0051   1.0000
  17.000   1.4079   0.10896   0.10560  -0.0606   0.0050   1.0000
  17.250   1.4000   0.11419   0.11094  -0.0628   0.0050   1.0000
  17.500   1.3917   0.11961   0.11647  -0.0651   0.0049   1.0000
  17.750   1.3837   0.12510   0.12206  -0.0676   0.0049   1.0000
  18.000   1.3751   0.13079   0.12787  -0.0703   0.0048   1.0000
  18.250   1.3671   0.13645   0.13363  -0.0731   0.0048   1.0000
  18.500   1.3580   0.14247   0.13977  -0.0763   0.0048   1.0000
  18.750   1.3497   0.14852   0.14591  -0.0797   0.0047   1.0000
  19.000   1.3399   0.15501   0.15252  -0.0834   0.0047   1.0000
  19.250   1.3305   0.16161   0.15924  -0.0873   0.0047   1.0000
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