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GOE 436 AIRFOIL (goe436-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 436 AIRFOIL (goe436-il)
Reynolds number: 200,000
Max Cl/Cd: 68.25 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe436-il-200000.txt
Download as CSV file: xf-goe436-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 436 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3683   0.09753   0.09393  -0.0405   1.0000   0.0662
  -9.000  -0.3887   0.09488   0.09138  -0.0423   1.0000   0.0665
  -8.750  -0.4153   0.09264   0.08924  -0.0421   1.0000   0.0666
  -8.500  -0.3819   0.08747   0.08403  -0.0377   1.0000   0.0679
  -8.250  -0.3776   0.08554   0.08214  -0.0349   1.0000   0.0687
  -8.000  -0.3851   0.08390   0.08056  -0.0322   1.0000   0.0695
  -7.750  -0.4037   0.08270   0.07944  -0.0287   1.0000   0.0700
  -7.500  -0.4234   0.08130   0.07812  -0.0258   1.0000   0.0705
  -7.250  -0.4368   0.07944   0.07631  -0.0240   1.0000   0.0714
  -7.000  -0.4359   0.07615   0.07301  -0.0263   0.9981   0.0733
  -6.750  -0.4146   0.06410   0.06054  -0.0477   0.9871   0.0796
  -6.500  -0.3869   0.06143   0.05795  -0.0488   0.9839   0.0810
  -6.250  -0.3601   0.05869   0.05518  -0.0511   0.9779   0.0832
  -6.000  -0.3278   0.05161   0.04740  -0.0620   0.9702   0.0932
  -5.750  -0.3036   0.04860   0.04453  -0.0628   0.9631   0.0948
  -5.500  -0.2692   0.04607   0.04200  -0.0657   0.9584   0.0977
  -5.250  -0.2420   0.04225   0.03756  -0.0694   0.9496   0.1085
  -5.000  -0.2093   0.03955   0.03499  -0.0715   0.9448   0.1112
  -4.750  -0.1691   0.03707   0.03202  -0.0757   0.9410   0.1242
  -4.500  -0.1446   0.03456   0.02960  -0.0760   0.9319   0.1267
  -4.250  -0.1082   0.02731   0.02122  -0.0778   0.9275   0.0952
  -4.000  -0.0709   0.02423   0.01772  -0.0794   0.9234   0.0870
  -3.750  -0.0426   0.02236   0.01554  -0.0793   0.9152   0.0863
  -3.500  -0.0035   0.02082   0.01373  -0.0811   0.9112   0.0878
  -3.250   0.0259   0.01964   0.01233  -0.0810   0.9029   0.0888
  -3.000   0.0617   0.01849   0.01098  -0.0821   0.8968   0.0901
  -2.750   0.0932   0.01780   0.01012  -0.0822   0.8885   0.0918
  -2.500   0.1259   0.01644   0.00869  -0.0829   0.8806   0.0948
  -2.250   0.1548   0.01572   0.00796  -0.0827   0.8702   0.0975
  -2.000   0.1887   0.01503   0.00722  -0.0834   0.8622   0.1006
  -1.750   0.2153   0.01458   0.00672  -0.0826   0.8493   0.1042
  -1.500   0.2429   0.01413   0.00622  -0.0821   0.8367   0.1078
  -1.250   0.2697   0.01350   0.00564  -0.0815   0.8238   0.1126
  -1.000   0.2969   0.01313   0.00525  -0.0809   0.8105   0.1179
  -0.750   0.3233   0.01278   0.00487  -0.0802   0.7965   0.1249
  -0.500   0.3482   0.01246   0.00458  -0.0792   0.7807   0.1347
  -0.250   0.3720   0.01214   0.00429  -0.0780   0.7630   0.1483
   0.000   0.3949   0.01171   0.00402  -0.0768   0.7436   0.1897
   0.250   0.4998   0.00948   0.00395  -0.0918   0.7186   1.0000
   0.500   0.5207   0.00954   0.00382  -0.0901   0.6931   1.0000
   0.750   0.5418   0.00966   0.00371  -0.0885   0.6664   1.0000
   1.000   0.5625   0.00985   0.00366  -0.0868   0.6386   1.0000
   1.250   0.5829   0.01008   0.00367  -0.0850   0.6104   1.0000
   1.500   0.6034   0.01034   0.00373  -0.0834   0.5840   1.0000
   1.750   0.6242   0.01060   0.00380  -0.0819   0.5601   1.0000
   2.000   0.6453   0.01086   0.00389  -0.0804   0.5392   1.0000
   2.250   0.6669   0.01110   0.00400  -0.0790   0.5207   1.0000
   2.500   0.6887   0.01137   0.00412  -0.0778   0.5051   1.0000
   2.750   0.7110   0.01165   0.00426  -0.0766   0.4920   1.0000
   3.000   0.7338   0.01192   0.00444  -0.0755   0.4804   1.0000
   3.250   0.7571   0.01220   0.00465  -0.0746   0.4704   1.0000
   3.750   0.8043   0.01281   0.00511  -0.0728   0.4529   1.0000
   4.000   0.8289   0.01319   0.00536  -0.0722   0.4458   1.0000
   4.250   0.8526   0.01345   0.00566  -0.0713   0.4386   1.0000
   4.500   0.8772   0.01379   0.00592  -0.0707   0.4318   1.0000
   4.750   0.9006   0.01409   0.00623  -0.0698   0.4235   1.0000
   5.000   0.9243   0.01442   0.00647  -0.0690   0.4148   1.0000
   5.250   0.9460   0.01464   0.00672  -0.0678   0.4046   1.0000
   5.500   0.9692   0.01496   0.00698  -0.0669   0.3957   1.0000
   5.750   0.9920   0.01519   0.00727  -0.0659   0.3882   1.0000
   6.000   1.0166   0.01555   0.00757  -0.0653   0.3823   1.0000
   6.250   1.0394   0.01581   0.00793  -0.0644   0.3757   1.0000
   6.500   1.0627   0.01608   0.00822  -0.0635   0.3691   1.0000
   6.750   1.0863   0.01642   0.00857  -0.0628   0.3630   1.0000
   7.000   1.1086   0.01667   0.00891  -0.0618   0.3561   1.0000
   7.250   1.1323   0.01701   0.00920  -0.0611   0.3496   1.0000
   7.500   1.1527   0.01720   0.00954  -0.0597   0.3419   1.0000
   7.750   1.1750   0.01747   0.00982  -0.0587   0.3351   1.0000
   8.000   1.1956   0.01772   0.01019  -0.0574   0.3274   1.0000
   8.250   1.2165   0.01796   0.01046  -0.0562   0.3199   1.0000
   8.500   1.2361   0.01820   0.01082  -0.0548   0.3114   1.0000
   8.750   1.2557   0.01846   0.01110  -0.0534   0.3034   1.0000
   9.000   1.2735   0.01866   0.01147  -0.0516   0.2933   1.0000
   9.250   1.2909   0.01892   0.01178  -0.0498   0.2834   1.0000
   9.500   1.3062   0.01918   0.01208  -0.0477   0.2716   1.0000
   9.750   1.3200   0.01945   0.01242  -0.0453   0.2565   1.0000
  10.000   1.3313   0.01977   0.01281  -0.0426   0.2358   1.0000
  10.250   1.3375   0.02031   0.01329  -0.0391   0.2104   1.0000
  10.500   1.3396   0.02123   0.01405  -0.0353   0.1788   1.0000
  10.750   1.3385   0.02252   0.01515  -0.0315   0.1498   1.0000
  11.000   1.3370   0.02399   0.01649  -0.0279   0.1277   1.0000
  11.250   1.3370   0.02547   0.01791  -0.0248   0.1114   1.0000
  11.500   1.3381   0.02697   0.01939  -0.0220   0.1002   1.0000
  11.750   1.3381   0.02861   0.02101  -0.0195   0.0917   1.0000
  12.000   1.3413   0.03015   0.02260  -0.0174   0.0846   1.0000
  12.250   1.3404   0.03205   0.02452  -0.0154   0.0795   1.0000
  12.500   1.3410   0.03398   0.02651  -0.0137   0.0747   1.0000
  12.750   1.3344   0.03659   0.02912  -0.0120   0.0709   1.0000
  13.000   1.3325   0.03899   0.03164  -0.0108   0.0670   1.0000
  13.250   1.3268   0.04188   0.03458  -0.0098   0.0634   1.0000
  13.500   1.3144   0.04553   0.03821  -0.0089   0.0602   1.0000
  13.750   1.3120   0.04846   0.04131  -0.0085   0.0567   1.0000
  14.000   1.3067   0.05173   0.04464  -0.0082   0.0538   1.0000
  14.250   1.3001   0.05502   0.04784  -0.0073   0.0505   1.0000
  14.500   1.2984   0.05820   0.05122  -0.0075   0.0480   1.0000
  14.750   1.2970   0.06131   0.05441  -0.0077   0.0454   1.0000
  15.000   1.2974   0.06406   0.05709  -0.0074   0.0430   1.0000
  15.250   1.2983   0.06697   0.06012  -0.0073   0.0411   1.0000
  15.500   1.2979   0.07022   0.06352  -0.0078   0.0393   1.0000
  15.750   1.2989   0.07324   0.06663  -0.0083   0.0377   1.0000
  16.000   1.3023   0.07590   0.06931  -0.0085   0.0364   1.0000
  16.250   1.3109   0.07777   0.07114  -0.0076   0.0351   1.0000
  16.500   1.3073   0.08171   0.07529  -0.0088   0.0342   1.0000
  16.750   1.3041   0.08561   0.07938  -0.0100   0.0332   1.0000
  17.000   1.3024   0.08934   0.08326  -0.0111   0.0323   1.0000
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