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GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 598 AIRFOIL (goe598-il)
Reynolds number: 100,000
Max Cl/Cd: 40.4 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe598-il-100000-n5.txt
Download as CSV file: xf-goe598-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 598 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4928   0.09793   0.09330  -0.0024   1.0000   0.0260
  -9.250  -0.4953   0.09335   0.08875  -0.0037   1.0000   0.0252
  -9.000  -0.6149   0.09894   0.09419   0.0029   1.0000   0.0193
  -8.750  -0.6143   0.09422   0.08952   0.0004   1.0000   0.0192
  -8.500  -0.6142   0.08936   0.08469  -0.0026   1.0000   0.0191
  -8.250  -0.6147   0.08432   0.07971  -0.0062   1.0000   0.0190
  -8.000  -0.6145   0.07870   0.07411  -0.0115   1.0000   0.0189
  -7.750  -0.6113   0.07267   0.06805  -0.0167   1.0000   0.0187
  -7.500  -0.6070   0.06674   0.06203  -0.0208   1.0000   0.0187
  -7.250  -0.6009   0.06087   0.05600  -0.0241   1.0000   0.0187
  -7.000  -0.5929   0.05517   0.05006  -0.0264   1.0000   0.0187
  -6.750  -0.5827   0.04969   0.04426  -0.0280   1.0000   0.0187
  -6.500  -0.5702   0.04449   0.03867  -0.0289   1.0000   0.0186
  -6.250  -0.5551   0.03962   0.03331  -0.0292   1.0000   0.0186
  -6.000  -0.5372   0.03522   0.02831  -0.0290   1.0000   0.0188
  -5.750  -0.5166   0.03144   0.02383  -0.0284   1.0000   0.0191
  -5.500  -0.4945   0.02818   0.01997  -0.0278   1.0000   0.0198
  -5.250  -0.4731   0.02558   0.01714  -0.0275   1.0000   0.0227
  -5.000  -0.4488   0.02339   0.01456  -0.0268   1.0000   0.0251
  -4.750  -0.4238   0.02129   0.01209  -0.0259   1.0000   0.0274
  -4.500  -0.3998   0.01958   0.01019  -0.0251   1.0000   0.0323
  -4.250  -0.3761   0.01812   0.00860  -0.0243   1.0000   0.0375
  -4.000  -0.3525   0.01698   0.00740  -0.0236   1.0000   0.0472
  -3.750  -0.3281   0.01622   0.00661  -0.0230   1.0000   0.0610
  -3.500  -0.3036   0.01543   0.00578  -0.0223   1.0000   0.0789
  -3.250  -0.2794   0.01467   0.00500  -0.0217   1.0000   0.1065
  -3.000  -0.2556   0.01390   0.00444  -0.0213   1.0000   0.1597
  -2.750  -0.2316   0.01319   0.00401  -0.0210   1.0000   0.2431
  -2.500  -0.2091   0.01216   0.00373  -0.0205   1.0000   0.4207
  -2.250  -0.1864   0.01162   0.00357  -0.0194   1.0000   0.5500
  -2.000  -0.1634   0.01126   0.00339  -0.0183   1.0000   0.6366
  -1.750  -0.1433   0.01082   0.00336  -0.0160   1.0000   0.7572
  -1.500  -0.1086   0.01052   0.00335  -0.0161   1.0000   0.9259
  -1.250  -0.0663   0.01046   0.00313  -0.0194   1.0000   1.0000
  -1.000  -0.0454   0.01049   0.00304  -0.0184   1.0000   1.0000
  -0.750  -0.0241   0.01055   0.00300  -0.0176   1.0000   1.0000
  -0.500  -0.0027   0.01064   0.00301  -0.0168   1.0000   1.0000
  -0.250   0.0312   0.01075   0.00303  -0.0186   0.9936   1.0000
   0.000   0.0708   0.01084   0.00306  -0.0215   0.9838   1.0000
   0.250   0.1103   0.01093   0.00313  -0.0243   0.9739   1.0000
   0.500   0.1492   0.01101   0.00321  -0.0270   0.9636   1.0000
   0.750   0.1871   0.01108   0.00331  -0.0293   0.9528   1.0000
   1.000   0.2238   0.01114   0.00342  -0.0313   0.9391   1.0000
   1.250   0.2582   0.01117   0.00354  -0.0326   0.9212   1.0000
   1.500   0.2920   0.01119   0.00363  -0.0336   0.9015   1.0000
   1.750   0.3236   0.01120   0.00371  -0.0339   0.8783   1.0000
   2.000   0.3529   0.01121   0.00381  -0.0336   0.8519   1.0000
   2.250   0.3801   0.01127   0.00393  -0.0328   0.8251   1.0000
   2.500   0.4062   0.01137   0.00409  -0.0319   0.7973   1.0000
   2.750   0.4316   0.01150   0.00434  -0.0308   0.7678   1.0000
   3.000   0.4562   0.01166   0.00456  -0.0295   0.7312   1.0000
   3.250   0.4792   0.01186   0.00475  -0.0277   0.6736   1.0000
   3.500   0.4929   0.01290   0.00461  -0.0238   0.4074   1.0000
   3.750   0.5068   0.01544   0.00545  -0.0224   0.0956   1.0000
   4.000   0.5283   0.01704   0.00672  -0.0214   0.0381   1.0000
   4.250   0.5521   0.01810   0.00792  -0.0205   0.0300   1.0000
   4.500   0.5753   0.01926   0.00919  -0.0196   0.0260   1.0000
   4.750   0.5982   0.02060   0.01066  -0.0187   0.0224   1.0000
   5.000   0.6216   0.02218   0.01239  -0.0176   0.0207   1.0000
   5.250   0.6460   0.02407   0.01451  -0.0166   0.0197   1.0000
   5.500   0.6711   0.02624   0.01694  -0.0156   0.0190   1.0000
   5.750   0.6950   0.02838   0.01938  -0.0148   0.0175   1.0000
   6.000   0.7161   0.03122   0.02253  -0.0141   0.0159   1.0000
   6.250   0.7354   0.03508   0.02689  -0.0130   0.0154   1.0000
   6.500   0.7539   0.03852   0.03083  -0.0119   0.0154   1.0000
   6.750   0.7708   0.04193   0.03470  -0.0108   0.0155   1.0000
   7.000   0.7863   0.04533   0.03856  -0.0097   0.0157   1.0000
   7.250   0.8000   0.04897   0.04267  -0.0085   0.0161   1.0000
   7.500   0.8087   0.05400   0.04827  -0.0074   0.0171   1.0000
   7.750   0.8110   0.06005   0.05477  -0.0070   0.0182   1.0000
   8.000   0.8099   0.06576   0.06077  -0.0073   0.0191   1.0000
   8.250   0.8056   0.07124   0.06646  -0.0084   0.0198   1.0000
   8.500   0.7978   0.07664   0.07199  -0.0102   0.0203   1.0000
   8.750   0.7869   0.08217   0.07759  -0.0133   0.0207   1.0000
   9.000   0.7785   0.08903   0.08447  -0.0194   0.0211   1.0000
   9.250   0.7736   0.09576   0.09116  -0.0248   0.0216   1.0000
   9.500   0.7703   0.10159   0.09695  -0.0284   0.0223   1.0000
   9.750   0.7683   0.10677   0.10210  -0.0308   0.0231   1.0000
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