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GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il)
Reynolds number: 1,000,000
Max Cl/Cd: 143.61 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe238-il-1000000.txt
Download as CSV file: xf-goe238-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 238 (HANSA-BRANDENBURG) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2233   0.09660   0.09366  -0.0437   0.6693   0.0199
  -9.250  -0.2242   0.09337   0.09041  -0.0459   0.6633   0.0200
  -9.000  -0.2217   0.09038   0.08742  -0.0475   0.6575   0.0200
  -8.750  -0.2130   0.08679   0.08382  -0.0475   0.6510   0.0202
  -8.500  -0.2046   0.08442   0.08141  -0.0478   0.6444   0.0203
  -8.250  -0.1968   0.08215   0.07914  -0.0483   0.6381   0.0204
  -8.000  -0.1896   0.08004   0.07702  -0.0488   0.6315   0.0207
  -7.750  -0.1848   0.07782   0.07478  -0.0493   0.6259   0.0209
  -7.500  -0.1824   0.07555   0.07253  -0.0497   0.6204   0.0211
  -7.250  -0.1823   0.07333   0.07031  -0.0502   0.6149   0.0213
  -7.000  -0.1754   0.07075   0.06770  -0.0520   0.6096   0.0218
  -6.750  -0.1667   0.06788   0.06482  -0.0543   0.6047   0.0224
  -6.500  -0.1563   0.06285   0.05972  -0.0615   0.6004   0.0235
  -6.250  -0.1416   0.05896   0.05575  -0.0647   0.5955   0.0236
  -6.000  -0.1313   0.05454   0.05127  -0.0666   0.5912   0.0238
  -5.750  -0.1154   0.05233   0.04904  -0.0671   0.5859   0.0239
  -5.500  -0.0979   0.05017   0.04682  -0.0678   0.5804   0.0241
  -5.250  -0.0790   0.04804   0.04463  -0.0687   0.5753   0.0243
  -5.000  -0.0588   0.04577   0.04230  -0.0698   0.5703   0.0246
  -4.750  -0.0377   0.04344   0.03988  -0.0708   0.5648   0.0250
  -4.500  -0.0155   0.04103   0.03738  -0.0719   0.5598   0.0257
  -4.250   0.0171   0.03611   0.03216  -0.0740   0.5560   0.0276
  -4.000   0.0350   0.03159   0.02745  -0.0745   0.5517   0.0280
  -3.750   0.0570   0.03014   0.02592  -0.0745   0.5466   0.0282
  -3.500   0.0803   0.02880   0.02450  -0.0745   0.5421   0.0285
  -3.250   0.1044   0.02739   0.02300  -0.0745   0.5374   0.0288
  -3.000   0.1289   0.02587   0.02137  -0.0744   0.5326   0.0294
  -2.750   0.1575   0.02349   0.01864  -0.0736   0.5281   0.0321
  -2.500   0.1799   0.02003   0.01478  -0.0729   0.5248   0.0326
  -2.250   0.2046   0.01881   0.01351  -0.0727   0.5201   0.0330
  -2.000   0.2299   0.01796   0.01258  -0.0724   0.5151   0.0334
  -1.750   0.2558   0.01721   0.01173  -0.0721   0.5102   0.0341
  -1.500   0.2823   0.01639   0.01081  -0.0718   0.5057   0.0352
  -1.250   0.3115   0.01664   0.01078  -0.0711   0.5010   0.0376
  -1.000   0.3349   0.01288   0.00659  -0.0699   0.4968   0.0319
  -0.750   0.3617   0.01191   0.00547  -0.0695   0.4927   0.0318
  -0.500   0.3890   0.01134   0.00479  -0.0692   0.4883   0.0321
  -0.250   0.4163   0.01097   0.00432  -0.0688   0.4842   0.0323
   0.000   0.4423   0.01010   0.00336  -0.0684   0.4803   0.0328
   0.250   0.4694   0.00974   0.00301  -0.0681   0.4774   0.0334
   0.500   0.4966   0.00953   0.00281  -0.0678   0.4742   0.0339
   0.750   0.5237   0.00935   0.00262  -0.0676   0.4708   0.0346
   1.000   0.5507   0.00921   0.00247  -0.0672   0.4674   0.0353
   1.250   0.5776   0.00914   0.00237  -0.0669   0.4636   0.0364
   1.500   0.6052   0.00904   0.00229  -0.0667   0.4605   0.0374
   1.750   0.6319   0.00883   0.00208  -0.0664   0.4569   0.0387
   2.000   0.6590   0.00876   0.00201  -0.0661   0.4536   0.0401
   2.250   0.6860   0.00875   0.00200  -0.0659   0.4501   0.0419
   2.500   0.7133   0.00875   0.00200  -0.0657   0.4472   0.0437
   2.750   0.7406   0.00866   0.00195  -0.0655   0.4448   0.0472
   3.000   0.7682   0.00866   0.00197  -0.0653   0.4418   0.0512
   3.250   0.7952   0.00863   0.00195  -0.0651   0.4369   0.0576
   3.500   0.8219   0.00867   0.00198  -0.0648   0.4326   0.0667
   3.750   0.8489   0.00855   0.00204  -0.0646   0.4301   0.1493
   4.000   0.9094   0.00695   0.00227  -0.0725   0.4237   1.0000
   4.250   0.9351   0.00706   0.00234  -0.0720   0.4188   1.0000
   4.500   0.9612   0.00715   0.00242  -0.0716   0.4144   1.0000
   4.750   0.9875   0.00722   0.00249  -0.0712   0.4099   1.0000
   5.000   1.0133   0.00733   0.00257  -0.0708   0.4047   1.0000
   5.250   1.0391   0.00744   0.00267  -0.0704   0.3988   1.0000
   5.500   1.0652   0.00753   0.00276  -0.0700   0.3923   1.0000
   5.750   1.0905   0.00769   0.00288  -0.0695   0.3854   1.0000
   6.000   1.1166   0.00778   0.00299  -0.0692   0.3780   1.0000
   6.250   1.1417   0.00795   0.00312  -0.0687   0.3663   1.0000
   6.500   1.1665   0.00815   0.00327  -0.0682   0.3508   1.0000
   6.750   1.1887   0.00856   0.00352  -0.0673   0.3160   1.0000
   7.000   1.2041   0.00955   0.00414  -0.0655   0.2521   1.0000
   7.250   1.2250   0.01007   0.00455  -0.0644   0.2305   1.0000
   7.500   1.2473   0.01046   0.00489  -0.0636   0.2177   1.0000
   7.750   1.2694   0.01086   0.00524  -0.0628   0.2064   1.0000
   8.000   1.2913   0.01127   0.00560  -0.0619   0.1922   1.0000
   8.250   1.3120   0.01176   0.00598  -0.0609   0.1702   1.0000
   8.500   1.3132   0.01366   0.00730  -0.0573   0.0810   1.0000
   8.750   1.3281   0.01447   0.00802  -0.0555   0.0644   1.0000
   9.000   1.3475   0.01493   0.00849  -0.0544   0.0603   1.0000
   9.250   1.3655   0.01546   0.00903  -0.0530   0.0570   1.0000
   9.500   1.3821   0.01604   0.00961  -0.0515   0.0535   1.0000
   9.750   1.4006   0.01647   0.01008  -0.0502   0.0522   1.0000
  10.000   1.4183   0.01691   0.01057  -0.0489   0.0508   1.0000
  10.250   1.4329   0.01744   0.01112  -0.0471   0.0489   1.0000
  10.500   1.4423   0.01805   0.01176  -0.0445   0.0472   1.0000
  10.750   1.4490   0.01885   0.01259  -0.0417   0.0451   1.0000
  11.000   1.4581   0.01965   0.01345  -0.0396   0.0438   1.0000
  11.250   1.4709   0.02037   0.01422  -0.0383   0.0428   1.0000
  11.500   1.4820   0.02135   0.01525  -0.0372   0.0415   1.0000
  11.750   1.4919   0.02260   0.01653  -0.0364   0.0397   1.0000
  12.000   1.4996   0.02420   0.01816  -0.0359   0.0378   1.0000
  12.250   1.5085   0.02578   0.01980  -0.0355   0.0363   1.0000
  12.500   1.5205   0.02708   0.02115  -0.0352   0.0347   1.0000
  12.750   1.5293   0.02872   0.02281  -0.0349   0.0327   1.0000
  13.000   1.5346   0.03071   0.02481  -0.0345   0.0302   1.0000
  13.250   1.5422   0.03247   0.02663  -0.0342   0.0285   1.0000
  13.500   1.5460   0.03461   0.02880  -0.0338   0.0266   1.0000
  13.750   1.5483   0.03691   0.03113  -0.0335   0.0245   1.0000
  14.000   1.5506   0.03922   0.03349  -0.0332   0.0230   1.0000
  14.250   1.5488   0.04195   0.03625  -0.0328   0.0214   1.0000
  14.500   1.5479   0.04463   0.03899  -0.0325   0.0206   1.0000
  14.750   1.5480   0.04720   0.04163  -0.0323   0.0197   1.0000
  15.000   1.5457   0.05009   0.04457  -0.0321   0.0188   1.0000
  15.250   1.5431   0.05313   0.04767  -0.0320   0.0181   1.0000
  15.500   1.5373   0.05661   0.05121  -0.0321   0.0173   1.0000
  15.750   1.5367   0.05953   0.05421  -0.0322   0.0169   1.0000
  16.000   1.5350   0.06261   0.05737  -0.0323   0.0165   1.0000
  16.250   1.5326   0.06584   0.06067  -0.0325   0.0160   1.0000
  16.500   1.5306   0.06904   0.06393  -0.0328   0.0156   1.0000
  16.750   1.5268   0.07251   0.06747  -0.0332   0.0152   1.0000
  17.000   1.5207   0.07629   0.07132  -0.0336   0.0148   1.0000
  17.250   1.5138   0.08026   0.07537  -0.0342   0.0145   1.0000
  17.500   1.5025   0.08491   0.08008  -0.0350   0.0140   1.0000
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