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GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 326 (PFALZ 55) AIRFOIL (goe326-il)
Reynolds number: 500,000
Max Cl/Cd: 104.63 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe326-il-500000.txt
Download as CSV file: xf-goe326-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 326 (PFALZ 55) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3340   0.08727   0.08517  -0.0236   1.0000   0.0207
  -7.500  -0.3310   0.08469   0.08264  -0.0244   1.0000   0.0211
  -7.250  -0.3281   0.08206   0.08005  -0.0256   1.0000   0.0215
  -7.000  -0.3134   0.07835   0.07636  -0.0304   0.9958   0.0224
  -6.750  -0.2688   0.07110   0.06902  -0.0487   0.9831   0.0245
  -6.500  -0.2331   0.06499   0.06282  -0.0592   0.9708   0.0247
  -6.250  -0.2160   0.05912   0.05691  -0.0632   0.9576   0.0252
  -6.000  -0.1959   0.05661   0.05435  -0.0645   0.9431   0.0258
  -5.750  -0.1750   0.05376   0.05141  -0.0667   0.9270   0.0266
  -5.500  -0.1524   0.05057   0.04810  -0.0695   0.9122   0.0278
  -5.250  -0.1093   0.04544   0.04261  -0.0767   0.8989   0.0310
  -5.000  -0.0892   0.03859   0.03550  -0.0799   0.8866   0.0317
  -4.750  -0.0696   0.03682   0.03367  -0.0801   0.8749   0.0324
  -4.500  -0.0471   0.03503   0.03177  -0.0805   0.8639   0.0333
  -4.250  -0.0221   0.03291   0.02949  -0.0812   0.8534   0.0350
  -4.000   0.0145   0.03135   0.02746  -0.0818   0.8425   0.0393
  -3.750   0.0363   0.02556   0.02133  -0.0831   0.8328   0.0408
  -3.500   0.0608   0.02412   0.01981  -0.0833   0.8226   0.0418
  -3.250   0.0865   0.02285   0.01841  -0.0834   0.8115   0.0433
  -3.000   0.1137   0.02154   0.01690  -0.0834   0.8010   0.0461
  -2.750   0.1450   0.02249   0.01747  -0.0825   0.7907   0.0501
  -2.500   0.1695   0.01812   0.01281  -0.0832   0.7813   0.0527
  -2.250   0.1964   0.01712   0.01171  -0.0832   0.7712   0.0544
  -2.000   0.2239   0.01630   0.01071  -0.0831   0.7616   0.0570
  -1.750   0.2530   0.01732   0.01154  -0.0825   0.7510   0.0627
  -1.500   0.2820   0.01340   0.00715  -0.0822   0.7420   0.0476
  -1.250   0.3099   0.01236   0.00591  -0.0819   0.7321   0.0463
  -1.000   0.3378   0.01167   0.00508  -0.0817   0.7214   0.0460
  -0.750   0.3657   0.01112   0.00444  -0.0815   0.7100   0.0460
  -0.500   0.3934   0.01078   0.00402  -0.0813   0.6983   0.0473
  -0.250   0.4210   0.01043   0.00360  -0.0810   0.6855   0.0481
   0.000   0.4486   0.01012   0.00323  -0.0808   0.6712   0.0489
   0.250   0.4763   0.00991   0.00297  -0.0806   0.6544   0.0498
   0.500   0.5036   0.00958   0.00258  -0.0804   0.6345   0.0512
   0.750   0.5308   0.00932   0.00225  -0.0802   0.6116   0.0537
   1.250   0.5849   0.00931   0.00203  -0.0798   0.5630   0.0616
   1.500   0.6119   0.00931   0.00193  -0.0796   0.5442   0.0687
   1.750   0.6392   0.00931   0.00190  -0.0794   0.5298   0.0926
   2.000   0.6646   0.00742   0.00208  -0.0794   0.5177   1.0000
   2.250   0.6917   0.00759   0.00214  -0.0792   0.5054   1.0000
   2.500   0.7188   0.00777   0.00222  -0.0790   0.4928   1.0000
   2.750   0.7458   0.00795   0.00231  -0.0788   0.4807   1.0000
   3.000   0.7732   0.00809   0.00240  -0.0787   0.4696   1.0000
   3.250   0.8005   0.00823   0.00250  -0.0786   0.4592   1.0000
   3.500   0.8276   0.00840   0.00261  -0.0785   0.4486   1.0000
   3.750   0.8546   0.00856   0.00274  -0.0783   0.4373   1.0000
   4.000   0.8818   0.00871   0.00286  -0.0782   0.4256   1.0000
   4.250   0.9087   0.00888   0.00299  -0.0781   0.4136   1.0000
   4.500   0.9355   0.00907   0.00314  -0.0779   0.4003   1.0000
   4.750   0.9621   0.00927   0.00330  -0.0777   0.3878   1.0000
   5.000   0.9885   0.00949   0.00348  -0.0775   0.3765   1.0000
   5.250   1.0149   0.00970   0.00367  -0.0774   0.3639   1.0000
   5.500   1.0409   0.00996   0.00388  -0.0771   0.3474   1.0000
   5.750   1.0667   0.01022   0.00408  -0.0769   0.3290   1.0000
   6.000   1.0925   0.01050   0.00432  -0.0766   0.3135   1.0000
   6.250   1.1178   0.01080   0.00456  -0.0763   0.2952   1.0000
   6.500   1.1426   0.01118   0.00486  -0.0759   0.2732   1.0000
   6.750   1.1672   0.01156   0.00516  -0.0756   0.2498   1.0000
   7.000   1.1908   0.01206   0.00553  -0.0751   0.2200   1.0000
   7.250   1.2113   0.01292   0.00608  -0.0742   0.1645   1.0000
   7.500   1.2303   0.01393   0.00682  -0.0732   0.1230   1.0000
   7.750   1.2524   0.01455   0.00738  -0.0725   0.1086   1.0000
   8.000   1.2747   0.01512   0.00789  -0.0719   0.0944   1.0000
   8.250   1.2960   0.01579   0.00843  -0.0711   0.0711   1.0000
   8.500   1.3082   0.01739   0.00965  -0.0691   0.0232   1.0000
   8.750   1.3278   0.01816   0.01046  -0.0680   0.0192   1.0000
   9.000   1.3476   0.01886   0.01127  -0.0669   0.0179   1.0000
   9.250   1.3658   0.01968   0.01219  -0.0656   0.0168   1.0000
   9.500   1.3815   0.02067   0.01328  -0.0639   0.0159   1.0000
   9.750   1.3930   0.02194   0.01468  -0.0618   0.0150   1.0000
  10.000   1.4042   0.02309   0.01594  -0.0596   0.0145   1.0000
  10.250   1.4151   0.02404   0.01699  -0.0574   0.0141   1.0000
  10.500   1.4225   0.02516   0.01820  -0.0548   0.0136   1.0000
  10.750   1.4280   0.02649   0.01962  -0.0522   0.0132   1.0000
  11.000   1.4318   0.02804   0.02128  -0.0498   0.0128   1.0000
  11.250   1.4346   0.02981   0.02314  -0.0477   0.0125   1.0000
  11.500   1.4363   0.03179   0.02523  -0.0459   0.0123   1.0000
  11.750   1.4368   0.03402   0.02756  -0.0444   0.0120   1.0000
  12.000   1.4360   0.03652   0.03015  -0.0430   0.0118   1.0000
  12.250   1.4334   0.03932   0.03304  -0.0419   0.0116   1.0000
  12.500   1.4301   0.04231   0.03611  -0.0408   0.0114   1.0000
  12.750   1.4261   0.04541   0.03929  -0.0396   0.0112   1.0000
  13.000   1.4227   0.04847   0.04242  -0.0380   0.0111   1.0000
  13.250   1.4235   0.05118   0.04522  -0.0367   0.0109   1.0000
  13.500   1.4251   0.05387   0.04806  -0.0366   0.0108   1.0000
  13.750   1.4259   0.05674   0.05106  -0.0366   0.0106   1.0000
  14.000   1.4257   0.05977   0.05424  -0.0367   0.0105   1.0000
  14.250   1.4246   0.06298   0.05759  -0.0368   0.0103   1.0000
  14.500   1.4228   0.06637   0.06111  -0.0371   0.0101   1.0000
  14.750   1.4201   0.06992   0.06480  -0.0374   0.0099   1.0000
  15.000   1.4168   0.07368   0.06869  -0.0379   0.0098   1.0000
  15.250   1.4127   0.07765   0.07280  -0.0385   0.0097   1.0000
  15.500   1.4075   0.08185   0.07714  -0.0393   0.0097   1.0000
  15.750   1.4012   0.08631   0.08175  -0.0404   0.0096   1.0000
  16.000   1.3939   0.09107   0.08666  -0.0418   0.0095   1.0000
  16.250   1.3854   0.09615   0.09189  -0.0435   0.0095   1.0000
  16.500   1.3758   0.10153   0.09743  -0.0455   0.0095   1.0000
  16.750   1.3651   0.10726   0.10332  -0.0478   0.0095   1.0000
  17.000   1.3535   0.11333   0.10955  -0.0505   0.0095   1.0000
  17.250   1.3410   0.11978   0.11617  -0.0537   0.0096   1.0000
  17.500   1.3279   0.12653   0.12308  -0.0572   0.0096   1.0000
  17.750   1.3140   0.13368   0.13040  -0.0612   0.0096   1.0000
  18.000   1.3001   0.14115   0.13802  -0.0655   0.0097   1.0000
  18.250   1.2852   0.14916   0.14619  -0.0704   0.0098   1.0000
  18.500   1.2702   0.15751   0.15470  -0.0757   0.0099   1.0000
  18.750   1.2547   0.16636   0.16369  -0.0814   0.0100   1.0000
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