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GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il)
Reynolds number: 500,000
Max Cl/Cd: 90.32 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe321-il-500000-n5.txt
Download as CSV file: xf-goe321-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 321 (HANSA-BRANDENBURG III.1) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3103   0.08827   0.08498  -0.0208   0.6898   0.0202
  -8.000  -0.3065   0.08432   0.08102  -0.0237   0.6846   0.0207
  -7.750  -0.3040   0.08039   0.07708  -0.0271   0.6796   0.0208
  -7.500  -0.2966   0.07488   0.07154  -0.0340   0.6750   0.0211
  -7.250  -0.2861   0.06839   0.06499  -0.0423   0.6700   0.0216
  -7.000  -0.2693   0.06632   0.06287  -0.0439   0.6639   0.0218
  -6.750  -0.2516   0.06390   0.06042  -0.0462   0.6582   0.0222
  -6.500  -0.2328   0.06090   0.05735  -0.0492   0.6518   0.0228
  -6.250  -0.2131   0.05704   0.05339  -0.0530   0.6460   0.0232
  -6.000  -0.1921   0.05267   0.04891  -0.0568   0.6398   0.0233
  -5.750  -0.1697   0.04839   0.04447  -0.0601   0.6331   0.0235
  -4.750  -0.0732   0.02553   0.02013  -0.0686   0.6078   0.0254
  -4.500  -0.0471   0.02426   0.01868  -0.0689   0.5999   0.0258
  -4.250  -0.0204   0.02335   0.01764  -0.0691   0.5923   0.0261
  -4.000   0.0064   0.02172   0.01578  -0.0692   0.5849   0.0264
  -3.750   0.0332   0.01915   0.01282  -0.0693   0.5787   0.0268
  -3.500   0.0607   0.01725   0.01058  -0.0693   0.5727   0.0273
  -3.250   0.0885   0.01591   0.00895  -0.0693   0.5675   0.0277
  -3.000   0.1167   0.01493   0.00775  -0.0693   0.5629   0.0281
  -2.750   0.1450   0.01417   0.00681  -0.0693   0.5575   0.0285
  -2.500   0.1733   0.01365   0.00611  -0.0692   0.5510   0.0290
  -2.250   0.2019   0.01325   0.00558  -0.0692   0.5444   0.0295
  -2.000   0.2303   0.01290   0.00512  -0.0692   0.5375   0.0297
  -1.750   0.2584   0.01239   0.00452  -0.0692   0.5317   0.0302
  -1.500   0.2868   0.01206   0.00418  -0.0693   0.5264   0.0306
  -1.250   0.3153   0.01183   0.00392  -0.0693   0.5212   0.0311
  -1.000   0.3437   0.01165   0.00369  -0.0694   0.5165   0.0316
  -0.750   0.3723   0.01145   0.00348  -0.0694   0.5115   0.0322
  -0.500   0.4009   0.01127   0.00328  -0.0695   0.5058   0.0328
  -0.250   0.4294   0.01114   0.00311  -0.0695   0.5010   0.0335
   0.000   0.4581   0.01102   0.00297  -0.0696   0.4971   0.0343
   0.250   0.4869   0.01089   0.00284  -0.0697   0.4923   0.0353
   0.500   0.5155   0.01078   0.00274  -0.0698   0.4866   0.0366
   0.750   0.5440   0.01073   0.00267  -0.0699   0.4821   0.0379
   1.000   0.5729   0.01065   0.00261  -0.0700   0.4779   0.0394
   1.250   0.6017   0.01060   0.00256  -0.0702   0.4721   0.0410
   1.500   0.6302   0.01058   0.00253  -0.0703   0.4652   0.0440
   1.750   0.6590   0.01054   0.00251  -0.0704   0.4578   0.0487
   2.000   0.6875   0.01054   0.00252  -0.0705   0.4498   0.0590
   2.250   0.7161   0.01051   0.00255  -0.0707   0.4410   0.0765
   2.500   0.7445   0.01051   0.00259  -0.0708   0.4305   0.1056
   2.750   0.7692   0.00861   0.00276  -0.0705   0.4160   1.0000
   3.000   0.7966   0.00882   0.00282  -0.0705   0.3914   1.0000
   3.250   0.8231   0.00915   0.00295  -0.0704   0.3605   1.0000
   3.500   0.8494   0.00951   0.00313  -0.0703   0.3356   1.0000
   3.750   0.8760   0.00982   0.00333  -0.0702   0.3174   1.0000
   4.000   0.9027   0.01012   0.00352  -0.0701   0.3026   1.0000
   4.250   0.9294   0.01041   0.00373  -0.0701   0.2892   1.0000
   4.500   0.9559   0.01071   0.00394  -0.0700   0.2755   1.0000
   4.750   0.9822   0.01102   0.00416  -0.0699   0.2613   1.0000
   5.250   1.0342   0.01169   0.00466  -0.0696   0.2311   1.0000
   5.500   1.0598   0.01205   0.00493  -0.0695   0.2165   1.0000
   5.750   1.0853   0.01240   0.00521  -0.0693   0.2047   1.0000
   6.000   1.1109   0.01272   0.00549  -0.0691   0.1967   1.0000
   6.250   1.1362   0.01306   0.00579  -0.0689   0.1901   1.0000
   6.500   1.1616   0.01338   0.00609  -0.0687   0.1857   1.0000
   6.750   1.1870   0.01367   0.00639  -0.0685   0.1824   1.0000
   7.000   1.2121   0.01399   0.00670  -0.0683   0.1794   1.0000
   7.250   1.2367   0.01432   0.00704  -0.0680   0.1767   1.0000
   7.500   1.2609   0.01469   0.00740  -0.0676   0.1743   1.0000
   7.750   1.2849   0.01505   0.00778  -0.0673   0.1722   1.0000
   8.000   1.3093   0.01536   0.00813  -0.0669   0.1711   1.0000
   8.250   1.3334   0.01568   0.00850  -0.0666   0.1700   1.0000
   8.500   1.3569   0.01602   0.00888  -0.0661   0.1686   1.0000
   8.750   1.3800   0.01639   0.00928  -0.0657   0.1666   1.0000
   9.000   1.4021   0.01680   0.00972  -0.0651   0.1638   1.0000
   9.250   1.4231   0.01728   0.01020  -0.0644   0.1608   1.0000
   9.500   1.4428   0.01782   0.01075  -0.0635   0.1582   1.0000
   9.750   1.4632   0.01827   0.01126  -0.0627   0.1566   1.0000
  10.000   1.4845   0.01864   0.01171  -0.0620   0.1553   1.0000
  10.250   1.5048   0.01904   0.01217  -0.0612   0.1535   1.0000
  10.500   1.5229   0.01950   0.01269  -0.0601   0.1510   1.0000
  10.750   1.5383   0.02005   0.01329  -0.0586   0.1486   1.0000
  11.000   1.5519   0.02074   0.01401  -0.0570   0.1456   1.0000
  11.250   1.5638   0.02161   0.01490  -0.0554   0.1423   1.0000
  11.500   1.5826   0.02210   0.01548  -0.0547   0.1390   1.0000
  11.750   1.5980   0.02283   0.01627  -0.0538   0.1344   1.0000
  12.000   1.6093   0.02392   0.01735  -0.0527   0.1288   1.0000
  12.250   1.6232   0.02488   0.01834  -0.0519   0.1188   1.0000
  12.500   1.6211   0.02730   0.02053  -0.0506   0.0877   1.0000
  12.750   1.6094   0.03082   0.02393  -0.0493   0.0656   1.0000
  13.000   1.6011   0.03416   0.02722  -0.0483   0.0495   1.0000
  13.250   1.5903   0.03781   0.03082  -0.0473   0.0350   1.0000
  13.500   1.5819   0.04128   0.03429  -0.0466   0.0255   1.0000
  13.750   1.5775   0.04441   0.03746  -0.0461   0.0212   1.0000
  14.000   1.5751   0.04738   0.04050  -0.0458   0.0190   1.0000
  14.250   1.5725   0.05045   0.04365  -0.0456   0.0176   1.0000
  14.500   1.5695   0.05362   0.04690  -0.0454   0.0165   1.0000
  14.750   1.5678   0.05672   0.05010  -0.0454   0.0158   1.0000
  15.000   1.5650   0.06007   0.05355  -0.0456   0.0151   1.0000
  15.250   1.5611   0.06365   0.05723  -0.0459   0.0146   1.0000
  15.500   1.5557   0.06749   0.06116  -0.0464   0.0141   1.0000
  15.750   1.5487   0.07164   0.06542  -0.0469   0.0137   1.0000
  16.000   1.5421   0.07580   0.06969  -0.0476   0.0133   1.0000
  16.250   1.5359   0.07996   0.07396  -0.0484   0.0131   1.0000
  16.500   1.5284   0.08438   0.07849  -0.0493   0.0128   1.0000
  16.750   1.5195   0.08909   0.08333  -0.0503   0.0125   1.0000
  17.000   1.5094   0.09409   0.08845  -0.0516   0.0123   1.0000
  17.250   1.4977   0.09939   0.09387  -0.0531   0.0121   1.0000
  17.500   1.4851   0.10497   0.09957  -0.0547   0.0119   1.0000
  17.750   1.4719   0.11078   0.10550  -0.0566   0.0117   1.0000
  18.000   1.4576   0.11685   0.11170  -0.0587   0.0115   1.0000
  18.250   1.4426   0.12314   0.11810  -0.0611   0.0114   1.0000
  18.500   1.4277   0.12952   0.12461  -0.0636   0.0113   1.0000
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